Integrated hydrogen energy supplementing unmanned aerial vehicle nest

Abstract

The application provides an integrated hydrogen energy supplement unmanned aerial vehicle nest, and relates to the technical field of hydrogen energy supplement unmanned aerial vehicles.The hydrogen energy supplement nest is provided with a top cover on both sides of the upper end, rollers are arranged on the bottom corners of the hydrogen energy supplement nest, a bearing plate is arranged on the inner wall of the hydrogen energy supplement nest, a unmanned aerial vehicle module is arranged on the surface of the bearing plate, the unmanned aerial vehicle module comprises a unmanned aerial vehicle body, the unmanned aerial vehicle body is located directly above the bearing plate, a fan blade frame is arranged on the surface of the unmanned aerial vehicle body, and a support frame is arranged on the lower surface of the unmanned aerial vehicle body.The application solves the problem that the unmanned aerial vehicle is inclined, the landing point is deviated or the unmanned aerial vehicle is hard-landed due to air flow disturbance, landing deviation or excessive impact during the landing and locking operation of the unmanned aerial vehicle, and further causes the locking mechanism to fail to be accurately aligned, the locking to fail or the structure to be damaged by impact.

Description

Technical Field

[0001] This invention relates to the field of hydrogen-powered refueling drone technology, and more particularly to an integrated hydrogen-powered refueling drone nest. Background Technology

[0002] The technological background of integrated hydrogen-powered drone refueling nests stems from the urgent global demand for clean energy and sustainable development. With the rapid development of drone technology, its application scenarios are becoming increasingly widespread, demonstrating its enormous potential in fields ranging from agricultural monitoring and environmental monitoring to logistics and delivery. The design concept of hydrogen-powered drone refueling nests is to combine hydrogen fuel cell technology with drone charging facilities, providing efficient hydrogen refueling for drones through automated nests, greatly extending their flight time and lifespan.

[0003] Existing technologies, such as the invention with publication number CN121553439A, disclose an outdoor inspection and refueling platform for hydrogen-powered drones. This patent includes a drone nest body, a landing platform mounted on its upper surface, a closed plate inside the nest body, adjusting rods on both sides of the nest body, and a shell attached to the end of each adjusting rod furthest from the nest body. A hydrogen tank is located inside the nest body. The drone body is placed on the upper surface of the landing platform, and refueling structures are located on both sides of the drone body. Each refueling structure includes two connecting pipes, both of which are fixedly connected to the drone body. The advantages of this invention are: it allows for convenient automatic hydrogen refueling of drones and enables cyclical use, avoiding the need for adapting to different environments on the nest, thus greatly improving the energy refueling efficiency of drones.

[0004] During the landing and locking operation of a drone, situations may arise where the drone tilts, deviates from its landing point, or makes a hard landing due to airflow disturbances, landing deviations, or excessive impacts. This can lead to problems such as the locking mechanism failing to align accurately, locking failure, or structural impact damage. Summary of the Invention

[0005] The purpose of this invention is to solve the shortcomings of the prior art in the process of using the landing locking operation of UAVs, such as the UAV tilting, landing point deviation or hard landing due to airflow disturbance, landing deviation or excessive impact, which leads to the locking mechanism being unable to be accurately aligned, locking failure or structural impact damage.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: an integrated hydrogen-powered refueling drone nest, comprising a hydrogen refueling nest, with top covers on both sides of the upper end of the hydrogen refueling nest, and rollers at the four corners of the bottom end of the hydrogen refueling nest. A support plate is provided on the upper end of the inner wall of the hydrogen refueling nest, and a drone module is mounted on the surface of the support plate. The drone module includes a drone body, which is located directly above the support plate. Fan blade frames are installed on all four sides of the drone body, and support frames are provided at the four corners of the lower surface of the drone body. A camera is mounted on the lower surface of the drone body. A docking mechanism is provided on the surface of the support plate corresponding to the positions of the support frames. The docking mechanism includes a... The system comprises a male connector, a mounting assembly, an airbag, and a connecting tube. The lower surface of the male connector is fixedly connected to the surface of the support plate via the mounting assembly. A female connector is fixedly connected to the bottom surface of the support frame. A movable piston is slidably connected to the inner wall of the male connector. Several through holes are formed on the upper arc surface of the male connector. Ball bearings are movably connected to the inner wall of the through holes. The cross-sectional dimensions of the ball bearings are adapted to the cross-sectional dimensions of the through holes. The inner wall of the female connector has a constricted cross-section and is inserted into the upper arc surface of the male connector. The four male connectors are arranged in pairs. A mating joint is fixedly connected to the side of each pair of male connectors that is close to each other. The inner walls of the two mating joints are fixedly connected to the two end surfaces of the airbag via the connecting tube.

[0007] The aforementioned components achieve the following effects: When the UAV lands, the female docking seat fits onto the upper end of the male docking seat. The inner wall of the constricted opening of the female seat compresses the ball bearings, causing them to move radially along the through hole, pushing the moving piston to slide within the male seat. Simultaneously, gas flows through the connecting pipe between the airbag and each male docking seat, achieving air pressure balance and linkage among the four support points. This structure can automatically complete the mechanical locking between the UAV and the nest, utilize the airbag to absorb the landing impact, and ensure uniform locking force at the four corners, preventing misalignment or jamming caused by minor deviations in the UAV's attitude. This significantly improves the reliability, synchronization, and buffering capacity of the docking, providing a stable base for subsequent hydrogen refueling.

[0008] Preferably, the mounting assembly includes a mounting plate, the surface of which is fixedly connected to one side surface of the male connector, and a mounting bracket is fixedly connected to the surface of the bearing plate at a position corresponding to the male connector. The inner wall of the mounting bracket is slidably inserted into the surface of the mounting plate, and the surfaces of the mounting plate and the mounting bracket are threaded through the same mounting shaft.

[0009] The aforementioned components achieve the following effect: by setting up the mounting plate, mounting bracket, and mounting shaft, the male connector and the support plate form a detachable plug-in fixed structure. This mounting assembly enables rapid positioning, installation, and replacement of the docking mechanism without the need for complete disassembly of the support plate. This facilitates maintenance, repair, and replacement with different specifications of male connectors for different models, reducing operating costs and downtime.

[0010] Preferably, the inner walls of the male docking seat are provided with inlay grooves on both sides, a spring is fixedly connected to the bottom of the inner wall of the inlay groove, a guide post is fixedly connected to the upper end of the spring, and a top groove is provided on the surface of the female docking seat, the inner wall of the top groove is inserted into the arc surface of the guide post.

[0011] The aforementioned components achieve the following effect: by incorporating an insert groove, spring, and guide post within the male docking seat, and creating a top groove on the surface of the female docking seat, the guide post retracts under pressure when the drone lands. Once the female docking seat is fully in place, the spring drives the guide post to automatically spring into the top groove. This structure assists in positioning, prevents accidental disengagement, and provides a tactile feedback / signal for positioning. Simultaneously, the spring buffers the longitudinal impact force during landing, preventing hard collisions that could damage the docking components, thus improving the safety and stability of the docking process.

[0012] Preferably, a sealing ring is fixedly connected to the bottom arc surface of the movable piston, and the surface of the sealing ring is slidably connected to the inner wall of the mating male seat.

[0013] The effect achieved by the above components is as follows: by fixing the sealing ring on the arc surface at the bottom of the moving piston and making the sealing ring slide in connection with the inner wall of the mating seat, the airtightness between the moving piston and the inner cavity of the mating seat can be guaranteed, preventing pressurized gas from leaking from the edge of the piston, thereby ensuring the effective transmission of gas pressure between the airbag and the mating seat, maintaining the accuracy of the locking force or buffering force, and avoiding locking failure due to air leakage.

[0014] Preferably, a signal receiver is fixedly connected to one side surface of the male docking seat, and a signal transmitter is fixedly connected to one side surface of the female docking seat. The signal receiver and the signal transmitter are electrically connected on their sides that are close to each other.

[0015] The aforementioned components achieve the following effect: by installing a signal receiver on the male docking seat and a signal transmitter on the female docking seat, and establishing an electrical connection between the two when they are close together, the system can detect and provide feedback on whether the docking is in place in real time. When the signal is connected, the control system can know that the UAV is in position and automatically start the hydrogen refueling program or illuminate the status indicator light; if the connection is not established, an alarm will be issued or refueling will be prohibited, effectively preventing safety risks caused by poor docking and realizing electrical interlocking and intelligent control of the docking status.

[0016] Preferably, a pressing mechanism is provided on one side of the two support frames that are close to each other. The pressing mechanism includes a connecting rod and a pressing plate. The two ends of the connecting rod are fixedly connected to the surface of the support frame. The arc surfaces of both ends of the connecting rod are threaded with a rotating shaft. A movable ring is rotatably connected to one side of the rotating shaft. A movable plate is fixedly connected to the bottom end of the movable ring. The pressing plate is located directly above the airbag. Both sides of the pressing plate are provided with mating grooves. The inner wall of the mating groove is inserted into the bottom surface of the movable plate.

[0017] The aforementioned components achieve the following effect: by setting a connecting rod, extrusion plate, rotating shaft, moving ring, and moving plate between two support frames, with the extrusion plate positioned directly above the airbag, the operator can rotate the rotating shaft to adjust the vertical position of the moving plate. This allows the bottom of the moving plate to insert into the mating groove of the extrusion plate, causing the extrusion plate to apply different levels of pre-pressure to the airbag. This extrusion mechanism can actively adjust the internal air pressure of the airbag according to the weight of the drone or the required locking force, thereby changing the force of the ball bearings pushing outwards and achieving stepless adjustment of the locking force to adapt to the parking needs of different models or different wind speed environments. Simultaneously, the mating groove insertion structure facilitates the disassembly and replacement of the extrusion plate.

[0018] Preferably, an auxiliary rod is fixedly connected to the surface of the support frame at the position corresponding to the movable plate, and the arc surface of the auxiliary rod slides through the surface of the movable plate.

[0019] The effect achieved by the above components is as follows: by setting an auxiliary rod on the surface of the support frame and allowing the arc surface of the auxiliary rod to slide through the surface of the moving plate, it can provide guidance and limit for the up and down movement of the moving plate, prevent the moving plate from tilting or rotating during the adjustment process, ensure that the extrusion plate presses against the airbag smoothly and vertically, and improve the accuracy and consistency of pressure transmission.

[0020] Preferably, a plurality of protrusions, which are hard rubber blocks, are fixedly connected to the lower surface of the extrusion plate. The effect achieved by the above component is as follows: by setting the protrusions on the lower surface of the extrusion plate as hard rubber blocks, the protrusions can increase the friction between the extrusion plate and the airbag, preventing relative sliding between the two during vibration or pressure changes, thereby stabilizing the compressed area of ​​the airbag; at the same time, the elasticity of the hard rubber can prevent excessive compression from damaging the airbag surface and extend the service life of the airbag.

[0021] Preferably, auxiliary mechanisms are provided on the four corner surfaces of the support plate. Each auxiliary mechanism includes a connecting hole, which is opened on the surface of the support plate. A guide frame is fixedly connected to the bottom of the inner wall of the connecting hole. An airflow pipe is fixedly connected to the bottom of the guide frame. A limit frame is fixedly connected to the upper end of the airflow pipe. An air pipe is fixedly connected to the surface of the docking seat. One end of the air pipe is inserted into the inner wall of the limit frame. A baffle is fixedly connected to the inner wall surface of the connecting hole.

[0022] The aforementioned components achieve the following effect: utilizing the downwash airflow generated by the rotor during UAV takeoff, the airflow is delivered to the docking male seat through the connecting hole, guide frame, airflow pipe, limit frame, and air pipe, pushing the moving piston upward to retract the ball bearing, thereby automatically unlocking the device. This achieves self-powered, highly reliable takeoff and unlocking without the need for external power.

[0023] Preferably, a guide frame is fixedly connected to the upper surface of the limiting frame, and the cross-sectional dimensions of the guide frame are adapted to the cross-sectional dimensions of the air tube.

[0024] The aforementioned components achieve the following effects: the guide frame guides the air tube to be accurately inserted into the limiting frame, preventing docking deviation, ensuring unobstructed airflow, and improving the stability and success rate of the unlocking function.

[0025] Compared with the prior art, the advantages and positive effects of the present invention are as follows: 1. In this invention, by setting up a docking mechanism, when the UAV lands, the docking female seat at the bottom of the support frame fits into the docking male seat on the bearing plate. The inner wall of the constricted opening of the female seat compresses the ball bearings, which push the moving piston to slide, forcing gas into the airbag through the connecting pipe. The airbag expands and absorbs the impact energy. At the same time, the ball bearings are pushed out from the inside by the piston and locked onto the inner wall of the constricted opening of the female seat, achieving self-locking. This design uses only the UAV's own gravity to complete the locking and buffering, without the need for external power such as motors or electromagnets. The purely mechanical pneumatic structure has high reliability, is impact-resistant, anti-skew, and adaptable to harsh outdoor environments such as high and low temperatures and humidity, significantly improving the automation and safety of the hydrogen refueling drone.

[0026] 2. In this invention, a compression mechanism is set up, with a connecting rod fixed between two support frames. A rotating shaft is threadedly connected to the connecting rod, driving the moving ring and moving plate to move up and down. The bottom end of the moving plate is inserted into the mating grooves on both sides of the compression plate, thereby changing the initial pre-compression of the airbag by the compression plate. The greater the pre-compression, the higher the initial air pressure inside the airbag, the greater the resistance that the moving piston needs to overcome during landing, and the greater the locking force of the outer edge of the ball bearing. The stepless adjustment of the locking force can be achieved through the rotating shaft, allowing the same airbag to be adapted to hydrogen-powered drones of different weights, and increasing the locking force under harsh conditions such as strong winds and vibrations to prevent accidental dislodgement. At the same time, the compression plate is inserted through the mating groove, allowing for quick disassembly and assembly without tools, facilitating maintenance and airbag replacement. Hard rubber protrusions increase friction, reduce wear, and extend the service life of the components.

[0027] 3. In this invention, an auxiliary mechanism is provided. The support plate has connecting holes at its four corners, with a guide frame fixed at the bottom of each hole. An airflow pipe connects to the bottom of the guide frame, and a limiting frame is provided at the top of the airflow pipe. An air pipe is fixed to the surface of the docking female seat. After the UAV lands, the air pipe inserts into the limiting frame to form a sealed air passage. When the UAV is ready to take off, the high-speed rotation of the rotor generates a strong downwash airflow. The airflow enters the connecting holes, converges through the guide frame, flows into the airflow pipe, then passes through the limiting frame and enters the airflow pipe again, finally being delivered into the docking female seat and docking male seat. The airflow pressure acts on the lower end face of the moving piston, pushing the piston upwards. After the piston moves upwards, the ball bearings lose their inner support and retract radially, disengaging from the inner wall of the docking female seat's constriction opening, automatically releasing the locking mechanism. Attached Figure Description

[0028] Figure 1 This invention presents a three-dimensional structural schematic diagram of an integrated hydrogen-powered refueling drone nest. Figure 2 A partial schematic diagram of a three-dimensional structure for an integrated hydrogen-powered refueling drone nest proposed in this invention; Figure 3 This invention presents an enlarged structural schematic diagram of point A of an integrated hydrogen-powered refueling drone's nest; Figure 4 This invention presents a partial cross-sectional structural diagram of a docking mechanism for an integrated hydrogen-powered refueling drone's nest; Figure 5 This invention presents an enlarged structural schematic diagram of point B of an integrated hydrogen-powered refueling drone's nest; Figure 6 This invention provides a schematic diagram of the disassembled structure of a docking mechanism for an integrated hydrogen-powered refueling drone nest; Figure 7 This invention provides a partial schematic diagram of a docking mechanism for an integrated hydrogen-powered refueling drone's nest; Figure 8 This invention provides a structural schematic diagram of an extrusion mechanism for an integrated hydrogen-powered refueling drone's nest; Figure 9 This invention presents a partial structural schematic diagram of an auxiliary mechanism for an integrated hydrogen-powered refueling drone's nest.

[0029] Legend: 1. Hydrogen refueling pod; 2. Top cover; 3. UAV module; 31. UAV body; 32. Fan blade holder; 33. Support frame; 34. Camera; 4. Roller; 5. Docking mechanism; 501. Female docking socket; 502. Male docking socket; 503. Signal receiver; 504. Signal transmitter; 505. Airbag; 506. Connecting pipe; 507. Connecting connector; 508. Moving piston; 509. Sealing ring; 510. Top groove; 511. Embedding groove; 512. Guide post; 51 3. Spring; 515. Ball bearing; 516. Through hole; 517. Mounting assembly; 5171. Mounting bracket; 5172. Mounting shaft; 5173. Mounting plate; 6. Extrusion mechanism; 61. Connecting rod; 62. Moving ring; 63. Rotating shaft; 64. Moving plate; 65. Auxiliary rod; 66. Docking groove; 67. Extrusion plate; 68. Protrusion; 7. Auxiliary mechanism; 71. Guide frame; 72. Airflow pipe; 73. Limiting frame; 74. Guide frame; 75. Connecting hole; 76. Baffle; 77. Air pipe. Detailed Implementation

[0030] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described below in conjunction with the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0031] Numerous specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways than those described herein, and therefore the invention is not limited to the specific embodiments disclosed in the following specification.

[0032] like Figure 1-9 As shown, the present invention provides an integrated hydrogen-powered refueling drone nest, including a hydrogen refueling nest 1. A top cover 2 is provided on both sides of the upper end of the hydrogen refueling nest 1. Rollers 4 are provided at the four corners of the bottom end of the hydrogen refueling nest 1. A support plate 8 is provided on the upper end of the inner wall of the hydrogen refueling nest 1. A drone module 3 is provided on the surface of the support plate 8. The drone module 3 includes a drone body 31, which is located directly above the support plate 8. Fan blade frames 32 are installed on all four sides of the drone body 31. Support frames 33 are provided at the four corners of the lower surface of the drone body 31. A camera 34 is provided on the lower surface of the drone body 31. A docking mechanism 5 is provided on the surface of the support plate 8 corresponding to the position of the support frame 33. A pressing mechanism 6 is provided on the side where the two support frames 33 are close to each other. Auxiliary mechanisms 7 are provided on the four corners of the support plate 8.

[0033] The following section will explain the specific setup and function of its docking mechanism 5, extrusion mechanism 6, and auxiliary mechanism 7.

[0034] like Figure 3 Figure 4 , Figure 5 , Figure 6 and Figure 7As shown, the docking mechanism 5 includes a male docking seat 502, a mounting assembly 517, an airbag 505, and a connecting pipe 506. The lower surface of the male docking seat 502 is fixedly connected to the surface of the support plate 8 via the mounting assembly 517. A female docking seat 501 is fixedly connected to the bottom surface of the support frame 33. A moving piston 508 is slidably connected to the inner wall of the male docking seat 502. Several through holes 516 are opened on the upper arc surface of the male docking seat 502. The inner wall of the through holes 516 is movably connected to... There is a ball bearing 515, the cross-sectional dimensions of which are adapted to the cross-sectional dimensions of the through hole 516. The inner wall of the mating female 501 is constricted, and the inner wall of the mating female 501 is inserted into the upper arc surface of the mating male 502. The four mating males 502 are arranged in pairs, and each pair of mating males 502 has a fixed connection to a connector 507 on the side closest to each other. The inner walls of the two connectors 507 are fixedly connected to the two end surfaces of the airbag 505 through the connecting pipe 506. When the UAV lands, the mating female 501 is fitted into the upper end of the mating male 502. The constricted inner wall of the female 501 squeezes the ball bearing 515, causing it to move radially along the through hole 516, pushing the moving piston 508 to slide inside the male 502. At the same time, gas flows between the airbag 505 and each mating male 502 through the connecting pipe 506, realizing air pressure balance and linkage between the four support points. This structure can automatically complete the mechanical locking between the UAV and the nest, using airbags 505 to absorb the landing impact and ensuring uniform locking force at the four corners. This prevents misalignment or jamming caused by minor deviations in the UAV's attitude, significantly improving the reliability, synchronization, and buffering capacity of the docking. It also provides a stable base for subsequent hydrogen refueling. The mounting component 517 includes a mounting plate 5173, the surface of which is fixedly connected to one side surface of the docking male seat 502. A mounting bracket 5171 is fixedly connected to the surface of the support plate 8 at the position corresponding to the docking male seat 502. The inner wall of the mounting bracket 5171 is slidably inserted into the surface of the mounting plate 5173. The surfaces of the mounting plate 5173 and the mounting bracket 5171 are threaded through the same mounting shaft 5172. By setting up the mounting plate 5173, the mounting bracket 5171, and the mounting shaft 5172, the docking male seat 502 and the support plate 8 form a detachable insertion and fixing structure. The installation component 517 enables the quick positioning, installation and replacement of the docking mechanism 5 without the need for complete disassembly of the bearing plate 8. This facilitates maintenance and repair or allows for the replacement of different specifications of the docking male seat 502 according to different models, reducing operation and maintenance costs and downtime. Both sides of the inner wall of the docking male seat 502 are provided with inlay grooves 511. A spring 513 is fixedly connected to the bottom of the inner wall of the inlay groove 511, and a guide post 512 is fixedly connected to the upper end of the spring 513. A top groove 510 is provided on the surface of the docking female seat 501, and the inner wall of the top groove 510 is inserted into the arc surface of the guide post 512.By incorporating an inlay groove 511, a spring 513, and a guide post 512 within the male docking seat 502, and creating a top groove 510 on the surface of the female docking seat 501, the guide post 512 retracts under pressure when the drone lands. Once the female docking seat 501 is fully in place, the spring 513 drives the guide post 512 to automatically spring into the top groove 510. This structure serves to assist in positioning, prevent accidental disengagement, and provide a tactile feedback / signal for positioning. Simultaneously, the spring 513 buffers the longitudinal impact force during landing, preventing hard collisions that could damage the docking components, thus improving the safety and stability of the docking process. A sealing ring 509 is fixedly connected to the bottom arc surface of the moving piston 508, and the surface of the sealing ring 509 is slidably connected to the inner wall of the male docking seat 502. By fixing a sealing ring 509 to the arc-shaped surface at the bottom of the moving piston 508 and making the sealing ring 509 slidably connected to the inner wall of the mating male seat 502, the airtightness between the moving piston 508 and the inner cavity of the male seat can be ensured, preventing pressurized gas from leaking from the piston edge. This ensures effective transmission of gas pressure between the airbag 505 and the male seat, maintains the accuracy of the locking force or buffering force, and avoids locking failure due to air leakage. A signal receiver 503 is fixedly connected to one side surface of the mating male seat 502, and a signal transmitter 504 is fixedly connected to one side surface of the mating female seat 501. The sides of the signal receiver 503 and the signal transmitter 504 that are close to each other are electrically connected. By setting the signal receiver 503 on the mating male seat 502 and the signal transmitter 504 on the mating female seat 501, and making the two electrically connected when they are close to each other, it is possible to detect and provide feedback on whether the mating is in place in real time. When the signal is connected, the control system can know that the drone is in position and then automatically start the hydrogen refueling program or light up the status indicator light; if the connection is not connected, an alarm will be issued or refueling will be prohibited, effectively preventing safety risks caused by poor docking and realizing electrical interlocking and intelligent control of the docking status.

[0035] like Figure 8As shown, the extrusion mechanism 6 includes a connecting rod 61 and an extrusion plate 67. Both ends of the connecting rod 61 are fixedly connected to the surface of the support frame 33. A rotating shaft 63 is threaded onto the arc surfaces of both ends of the connecting rod 61. A movable ring 62 is rotatably connected to one side of the rotating shaft 63. A movable plate 64 is fixedly connected to the bottom end of the movable ring 62. The extrusion plate 67 is located directly above the airbag 505. Both sides of the extrusion plate 67 have mating grooves 66, and the inner walls of the mating grooves 66 are inserted into the bottom surface of the movable plate 64. By setting the connecting rod 61, extrusion plate 67, rotating shaft 63, movable ring 62, and movable plate 64 between the two support frames 33, and positioning the extrusion plate 67 directly above the airbag 505, the operator can rotate the rotating shaft 63 to adjust the vertical position of the movable plate 64, thereby inserting the bottom of the movable plate 64 into the mating groove 66 of the extrusion plate 67, causing the extrusion plate 67 to apply different degrees of pre-pressure to the airbag 505. The extrusion mechanism 6 can actively adjust the internal air pressure of the airbag 505 according to the weight of the drone or the required locking force, thereby changing the force of the ball bearing 515 pushing outward, realizing stepless adjustment of the locking force to adapt to the parking needs of different models or different wind speed environments. At the same time, the docking groove 66 plug-in structure facilitates the disassembly and replacement of the extrusion plate 67. An auxiliary rod 65 is fixedly connected to the surface of the support frame 33 at the position corresponding to the moving plate 64. The arc surface of the auxiliary rod 65 slides through the surface of the moving plate 64. By setting the auxiliary rod 65 on the surface of the support frame 33 and making the arc surface of the auxiliary rod 65 slide through the surface of the moving plate 64, it can provide guidance and limit for the up and down movement of the moving plate 64, preventing the moving plate 64 from tilting or rotating during the adjustment process, ensuring that the extrusion plate 67 presses against the airbag 505 smoothly and vertically, improving the accuracy and consistency of pressure transmission. Several protrusions 68 are fixedly connected to the lower surface of the extrusion plate 67. The protrusions 68 are hard rubber blocks. By setting the protrusion 68 on the lower surface of the extrusion plate 67 as a hard rubber block, the protrusion 68 can increase the friction between the extrusion plate 67 and the airbag 505, and prevent the two from sliding relative to each other when there is vibration or pressure change, thereby stabilizing the compressed area of ​​the airbag 505; at the same time, the elasticity of the hard rubber can prevent excessive compression from damaging the surface of the airbag 505 and extend the service life of the airbag 505.

[0036] like Figure 2 , Figure 4 , Figure 7 and Figure 9As shown, the auxiliary mechanism 7 includes a connecting hole 75, which is formed on the surface of the support plate 8. A guide frame 71 is fixedly connected to the bottom of the inner wall of the connecting hole 75. An airflow pipe 72 is fixedly connected to the bottom of the guide frame 71. A limit frame 73 is fixedly connected to the upper end of the airflow pipe 72. An air pipe 77 is fixedly connected to the surface of the docking female seat 501. One end of the air pipe 77 has an arc surface that is inserted into the inner wall of the limit frame 73. A baffle 76 is fixedly connected to the inner wall surface of the connecting hole 75. The downwash airflow generated by the rotor during UAV takeoff is sent to the docking male seat 502 through the connecting hole 75, guide frame 71, airflow pipe 72, limit frame 73, and air pipe 77. This pushes the moving piston 508 upward, causing the ball bearing 515 to retract, thereby automatically unlocking the machine. This achieves self-powered, highly reliable takeoff and unlocking without external power. A guide frame 74 is fixedly connected to the upper surface of the limit frame 73. The cross-sectional dimensions of the guide frame 74 are adapted to the cross-sectional dimensions of the air pipe 77. The guide frame 74 guides the air tube 77 to be accurately inserted into the limiting frame 73, preventing docking deviation, ensuring unobstructed airflow, and improving the stability and success rate of the unlocking function.

[0037] The overall working principle is as follows: When the UAV returns and lands above the support plate 8 of the hydrogen refueling nest 1, the docking females 501 fixed at the bottom of the four support frames 33 are aligned and fitted into the corresponding four docking males 502 on the support plate 8. As the UAV continues to descend, the constricted structure on the inner wall of the docking female 501 first contacts the ball bearing 515 at the upper arc surface of the docking male 502. Since the ball bearing 515 is movably installed in the through hole 516 and initially protrudes from the surface of the male, the constricted slope of the female applies a radially inward compressive force to the ball bearing 515, forcing the ball bearing 515 to move inward along the through hole 516. The inwardly moving ball bearing 515 then pushes the moving piston 508 inside the docking male 502 to slide downward. When the moving piston 508 moves downward, it forces the gas in the inner cavity of the male docking seat 502 into the airbag 505 through the connector 507 and the connecting pipe 506. The airbag 505 then expands, absorbing the impact energy generated by the drone's landing and providing a cushioning and shock absorption effect. When the female docking seat 501 is fully engaged, the moving piston 508 is stabilized at a certain equilibrium position by the counter-pressure of the gas in the airbag 505 and the action of its own sealing ring 509 and friction. At this time, the ball bearing 515 is pushed out from the inside by the moving piston 508, protruding again from the through hole 516 and tightly locked onto the constricted inner wall of the female docking seat 501, forming a mechanical self-locking mechanism. At the same time, the spring 513 in the groove 511 inside the male docking seat 502 pushes the guide post 512 upward into the top groove 510 of the female docking seat 501, achieving auxiliary positioning and preventing disengagement. When the female connector 501 and the male connector are close together, the signal receiver 503 and the signal transmitter 504 establish an electrical connection and send feedback to the control system that they are locked in place, and then hydrogen replenishment can begin. After the drone is reliably locked and secured to the support plate 8, the hydrogen refueling station 1 safely refuels the drone's hydrogen fuel cell or hydrogen storage device through the refueling interface. During the refueling process, the locking mechanism remains locked to prevent the drone from shifting due to accidental vibration or airflow disturbance. After hydrogen refueling is completed, the UAV prepares for takeoff. At this time, the UAV starts all rotors, and the fan blade frame 32 rotates at high speed, generating a strong downward airflow, i.e., a downwash airflow. This airflow blows vertically downwards onto the surface of the support plate 8 and enters the connecting holes 75 at the four corners of the support plate 8. After being converged by the guide frame 71, the airflow flows downwards into the airflow pipe 72, and then through the limiting frame 73 into the air pipe 77, which is fixedly connected to the surface of the docking female 501. The air pipe 77 is connected to the internal air passage of the docking male 502, so the airflow is ultimately sent into the interior of the docking male 502 and directly acts on the lower end face of the moving piston 508. As the rotor speed gradually increases, when the pressure generated by the downwash airflow is sufficient to overcome the holding force of the moving piston 508 in the locked state, the moving piston 508 is pushed upwards. After the piston moves upwards, the supporting force that originally held the ball 515 from the inside disappears, and the ball 515 can freely retract radially inwards along the through hole 516, thus completely detaching from the constricted inner wall of the docking female 501. At this point, the mechanical locking is released. Simultaneously, the guide post 512 is compressed and retracted by the top groove 510 during the initial ascent of the docking base 501, thus not hindering separation. The UAV then takes off vertically and leaves the pod. The entire unlocking process is completed entirely using the UAV's own takeoff airflow, requiring no additional power, air, or hydraulic power from the pod, achieving self-powered, zero-energy-consumption, and delay-free automatic unlocking. When it is necessary to adapt to drones of different weights or to increase the locking force in inclement weather, maintenance personnel can manually adjust the compression mechanism 6. By rotating the rotating shafts 63 at both ends of the connecting rod 61, the rotating shafts 63 drive the moving ring 62 and the moving plate 64 to move up and down. The bottom end of the moving plate 64 inserts into the mating groove 66 of the compression plate 67, thereby changing the initial pre-pressure of the compression plate 67 on the airbag 505. The greater the pre-pressure, the higher the initial air pressure of the airbag 505, the greater the resistance that the moving piston 508 needs to overcome during landing, and the greater the locking force of the outer edge of the ball bearing 515. Conversely, reducing the pre-pressure results in a smaller locking force. The hard rubber protrusions 68 on the lower surface of the compression plate 67 prevent slippage, and the auxiliary rod 65 ensures that the moving plate 64 rises and falls smoothly. This adjustment mechanism enables the drone nest to be safely compatible with different specifications of hydrogen-powered drones.

[0038] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any other way. Any person skilled in the art may make changes or modifications to the above-disclosed technical content to create equivalent embodiments for application in other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the protection scope of the present invention.

Claims

1. An integrated hydrogen-powered refueling drone nest, comprising a hydrogen refueling nest (1), characterized in that: The hydrogen refueling nest (1) is provided with top covers (2) on both sides of the upper end. Rollers (4) are provided at the four corners of the bottom end of the hydrogen refueling nest (1). A support plate (8) is provided on the upper end of the inner wall of the hydrogen refueling nest (1). A drone module (3) is provided on the surface of the support plate (8). The drone module (3) includes a drone body (31). The drone body (31) is located directly above the support plate (8). Fan blade frames (32) are installed on all four sides of the drone body (31). Support frames (33) are provided at the four corners of the lower surface of the drone body (31). A camera (34) is provided on the lower surface of the drone body (31). A docking mechanism (5) is provided on the surface of the support plate (8) at the position corresponding to the support frame (33). The docking mechanism (5) includes a docking male seat (502), an installation component (517), an airbag (505), and a connecting pipe (506). The lower part of the docking male seat (502) is... The surface is fixedly connected to the surface of the support plate (8) by means of the mounting component (517). The bottom surface of the support frame (33) is fixedly connected to the mating female seat (501). The inner wall of the mating male seat (502) is slidably connected to the moving piston (508). The upper arc surface of the mating male seat (502) is provided with several through holes (516). The inner wall of the through holes (516) is movably connected to the ball (515). The cross-sectional dimensions of the ball (515) are the same as those of the through holes (516). The cross-sectional dimensions of 16) are compatible. The inner wall of the docking female (501) is constricted. The inner wall of the docking female (501) is inserted into the upper arc surface of the docking male (502). The four docking males (502) are in pairs. Each pair of docking males (502) is fixedly connected to a connector (507) on the side close to each other. The inner walls of the two connectors (507) are fixedly connected to the two end surfaces of the airbag (505) through the connecting pipe (506).

2. The integrated hydrogen-powered refueling drone nest according to claim 1, characterized in that: The mounting assembly (517) includes a mounting plate (5173), the surface of which is fixedly connected to one side surface of the male connector (502), and a mounting bracket (5171) is fixedly connected to the surface of the bearing plate (8) at the position corresponding to the male connector (502). The inner wall of the mounting bracket (5171) is slidably inserted into the surface of the mounting plate (5173), and the surfaces of the mounting plate (5173) and the mounting bracket (5171) are threaded through the same mounting shaft (5172).

3. The integrated hydrogen-powered refueling drone nest according to claim 1, characterized in that: The male docking seat (502) has inlay grooves (511) on both sides of its inner wall. A spring (513) is fixedly connected to the bottom of the inner wall of the inlay groove (511). A guide post (512) is fixedly connected to the upper end of the spring (513). A top groove (510) is opened on the surface of the female docking seat (501). The inner wall of the top groove (510) is inserted into the arc surface of the guide post (512).

4. The integrated hydrogen-powered refueling drone nest according to claim 1, characterized in that: A sealing ring (509) is fixedly connected to the bottom arc surface of the movable piston (508), and the surface of the sealing ring (509) is slidably connected to the inner wall of the mating male seat (502).

5. The integrated hydrogen-powered refueling drone nest according to claim 1, characterized in that: A signal receiver (503) is fixedly connected to one side surface of the male docking seat (502), and a signal transmitter (504) is fixedly connected to one side surface of the female docking seat (501). The signal receiver (503) and the signal transmitter (504) are electrically connected to each other on the side closest to each other.

6. The integrated hydrogen-powered refueling drone nest according to claim 1, characterized in that: A pressing mechanism (6) is provided on one side of the two support frames (33) that are close to each other. The pressing mechanism (6) includes a connecting rod (61) and a pressing plate (67). The two ends of the connecting rod (61) are fixedly connected to the surface of the support frame (33). The arc surfaces of the two ends of the connecting rod (61) are threadedly connected to a rotating shaft (63). A moving ring (62) is rotatably connected to one side of the rotating shaft (63). A moving plate (64) is fixedly connected to the bottom end of the moving ring (62). The pressing plate (67) is located directly above the airbag (505). Both sides of the pressing plate (67) are provided with a mating groove (66). The inner wall of the mating groove (66) is inserted into the bottom surface of the moving plate (64).

7. The integrated hydrogen-powered refueling drone nest according to claim 6, characterized in that: An auxiliary rod (65) is fixedly connected to the surface of the support frame (33) at the position corresponding to the moving plate (64), and the arc surface of the auxiliary rod (65) slides through the surface of the moving plate (64).

8. The integrated hydrogen-powered refueling drone nest according to claim 6, characterized in that: The lower surface of the extrusion plate (67) is fixedly connected with a number of protrusions (68), which are hard rubber blocks.

9. The integrated hydrogen-powered refueling drone nest according to claim 1, characterized in that: Auxiliary mechanisms (7) are provided on the four corner surfaces of the support plate (8). The auxiliary mechanism (7) includes a connecting hole (75). The connecting hole (75) is opened on the surface of the support plate (8). A guide frame (71) is fixedly connected to the bottom of the inner wall of the connecting hole (75). An airflow pipe (72) is fixedly connected to the bottom of the guide frame (71). A limit frame (73) is fixedly connected to the upper end of the airflow pipe (72). An air pipe (77) is fixedly connected to the surface of the docking female seat (501). One end of the air pipe (77) is inserted into the inner wall of the limit frame (73). A baffle (76) is fixedly connected to the inner wall surface of the connecting hole (75).

10. An integrated hydrogen-powered refueling drone nest according to claim 9, characterized in that: The upper surface of the limiting frame (73) is fixedly connected to a guide frame (74), and the cross-sectional dimensions of the guide frame (74) are adapted to the cross-sectional dimensions of the air tube (77).

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