Lightweight hydrogen energy unmanned aerial vehicle energy supplementing device

Abstract

The present application provides a kind of lightweight hydrogen energy unmanned vehicle energy supplement equipment, it is related to lightweight hydrogen energy unmanned vehicle energy supplement technical field, including unmanned vehicle body and docking device, the bottom of unmanned vehicle body is provided with support frame, support frame is provided with mounting bracket corresponding to the position of unmanned vehicle body upper end surface, the upper end of mounting bracket is provided with hydrogen tank, the upper end surface of mounting bracket is provided with adjusting device, the surface around the upper end of unmanned vehicle body is all installed with fan blade frame, adjusting device includes two fixed frames and synchronous belt.The present application solves the operation and use process in the position of hydrogen tank is adjusted to realize the operation and use process with unmanned vehicle body, will appear manual adjustment laborious, moving is not stable, cannot accurately control docking position or extreme position is prone to impact situation, in turn lead to docking success rate is low, hydrogen leakage risk increases, equipment structure is easily damaged and the problem of energy supplement efficiency decline.

Description

Technical Field

[0001] This invention relates to the field of lightweight hydrogen-powered drone refueling technology, and more particularly to a lightweight hydrogen-powered drone refueling device. Background Technology

[0002] With the increasing global demand for clean energy, hydrogen energy, as an efficient and environmentally friendly energy carrier, is gradually becoming an important direction for the development of drone technology. Lightweight hydrogen-powered drone refueling equipment significantly improves the flight time and operating range of drones by using hydrogen fuel cell systems. This equipment typically includes a hydrogen storage tank, a fuel cell, a control system, and a power supply module.

[0003] Existing technologies, such as the invention with publication number CN106005464A, disclose an energy-saving drone energy replenishment device. This patent includes a shock-absorbing device, a support device, a docking base, and a charging device. The support device comprises eight units, each located along the central axis of the shock-absorbing device at its outer end, and connected to the shock-absorbing device by bolts. The docking base is located directly above the shock-absorbing device and is fixedly connected to it. The charging device is located above the docking base. This invention integrates photovoltaic energy storage, dual shock absorption, fixed docking, and multi-station charging, achieving multi-functionality for a single drone. It solves the problems of difficult and costly drone energy replenishment, extends the drone's flight time, and enhances its operational capabilities.

[0004] During the operation of adjusting the position of the hydrogen tank to dock or detach from the drone, issues such as laborious manual adjustment, unstable movement, inability to accurately control the docking position, or impact at extreme positions may occur. These issues can lead to low docking success rate, increased risk of hydrogen leakage, easy damage to equipment structure, and reduced refueling efficiency. Summary of the Invention

[0005] The purpose of this invention is to address the shortcomings of existing technologies where adjusting the position of hydrogen tanks to dock or detach from the drone body can result in laborious manual adjustments, unstable movement, inability to precisely control the docking position, or impacts at extreme positions. These issues lead to low docking success rates, increased risk of hydrogen leakage, easy damage to equipment structure, and decreased refueling efficiency.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a lightweight hydrogen-powered drone refueling device, comprising a drone body and a docking device, wherein a support frame is provided at the bottom end of the drone body, and a mounting frame is provided at the position corresponding to the upper surface of the drone body. A hydrogen tank is provided at the upper end of the mounting frame, and an adjustment device is provided on the upper surface of the mounting frame. Fan blade frames are installed on all four sides of the upper surface of the drone body. The adjustment device includes two fixed frames and a timing belt. The lower surfaces of the two fixed frames are fixedly connected to both sides of the surface of the mounting frame. A drive shaft is rotatably connected to the inner wall, and a second synchronous pulley is fixedly connected to one end of the drive shaft. A servo motor is fixedly connected to the surface of the mounting frame, and two first synchronous pulleys are fixedly connected to the output end of the servo motor. The two first synchronous pulleys are connected to the second synchronous pulley via a synchronous belt. A movable frame is threadedly connected to the arc surface of the drive shaft, and the upper ends of the two movable frames are rotatably connected to the same rotating frame. The inner wall of the rotating frame is fixedly connected to the hydrogen tank via a docking device. A support frame is fixedly connected to one side surface of the rotating frame, and the inner wall of the support frame abuts against one end of the hydrogen tank. The effects achieved by the above components are as follows: the adjustment device drives the synchronous belt through the servo motor, enabling the movable frame and rotating frame to move smoothly and accurately adjust the position of the hydrogen tank, facilitating docking or separation with the UAV body; at the same time, the support frame provides abutment support to the end of the hydrogen tank, improving the stability and safety of the hydrogen tank during movement and docking; the overall structure is lightweight and easy to integrate into the UAV refueling system.

[0007] Preferably, rotating frames are rotatably connected to both sides of the rotating frame. The rotating frames have an "L"-shaped cross-section, and a fixed roller is fixedly connected to one end of the mounting frame. The two arc surfaces of the fixed roller are rotatably connected to the transmission frame. The effect achieved by the above components is that by setting the L-shaped rotating frame and the transmission frame rotatably connected to the fixed roller, the rotating frame obtains stable rotational support when moving and changing angles, preventing the hydrogen tank from shaking. At the same time, the cooperation between the transmission frame and the fixed roller enhances the motion synchronization and structural strength of the rotating frame during the adjustment process.

[0008] Preferably, a first spring is slidably connected to one end of the drive shaft via an arc surface. One end of the first spring is fixedly connected to the inner wall surface of the fixed frame, and a protective ring is fixedly connected to the other end of the first spring. The effect achieved by the above components is that by providing a first spring and a protective ring on the drive shaft, buffer protection can be provided when the moving frame moves to its limit position, reducing impact noise and component wear, extending the service life of the drive shaft and the fixed frame, and preventing the moving frame from being damaged due to overtravel.

[0009] Preferably, guide rods are fixedly connected to both sides of the movable frame, and guide grooves are formed on the side wall surface of the fixed frame. The inner wall of the guide groove is slidably connected to the arc surface of the guide rod. The effect achieved by the above components is that the sliding cooperation between the guide rod and the guide groove provides precise linear motion guidance for the movable frame, avoids deflection or jamming during movement, ensures the repeatability of the hydrogen tank docking position, and improves the operational reliability of the adjustment device.

[0010] Preferably, a positioning device is provided on the surface of the support frame corresponding to the bottom end of the mounting frame. The positioning device includes two positioning frames, each with a U-shaped cross-section. The two positioning frames are located on opposite sides of the bottom end of the support frame. The inner wall of each positioning frame is fixedly connected to the surface of the support frame. A connecting frame with an L-shaped cross-section is rotatably connected to one side of the inner wall of each positioning frame. Positioning plates are fixedly connected to both sides of the bottom end of the support frame. Positioning blocks are fixedly connected to the surface of each positioning plate. The surface of each positioning block is inserted into the upper inner wall of the connecting frame. A positioning shaft is threaded through the upper surface of the connecting frame, and the bottom arc surface of the positioning shaft is threaded through the surface of the positioning block. The effect achieved by the above components is that the positioning device, through the insertion and cooperation of the positioning frames, connecting frames, and positioning blocks, and the threaded locking by the positioning shaft, can quickly fix the support frame to the UAV body or external platform, achieving stable installation of the refueling equipment. The insertion structure of the L-shaped connecting frame and the positioning block facilitates disassembly and assembly, improving the efficiency of equipment maintenance and hydrogen tank replacement.

[0011] Preferably, the inner wall of the positioning frame is provided with an adjusting plate, and adjusting columns and inlay columns are fixedly connected to both ends of the adjusting plate, respectively. A sliding groove is formed on the side wall surface of the positioning frame corresponding to the position of the adjusting column, and an inlay hole is formed on the side wall surface of the positioning frame corresponding to the position of the inlay column. The inner wall of the inlay hole is slidably connected to the arc surface of the inlay column, and the inner wall of the sliding groove is slidably connected to the arc surface of the adjusting column. An auxiliary shaft is fixedly connected to the bottom inner wall of the connecting frame, and a chuck is fixedly connected to the arc surface of the auxiliary shaft. Two slots are formed on the surface of the chuck, and the two slots are distributed at a 90° angle on the surface of the chuck. The inner wall of one of the slots engages with the arc surface of the adjusting column. The effect achieved by the above components is that, through the cooperation of the adjusting plate, adjusting column, inlay column, and the 90° angled slot on the chuck, the connecting frame can switch and lock between two working angles; the engagement structure between the adjusting column and the slot ensures stability after angle switching, thereby adapting to the energy replenishment operation requirements under different postures and enhancing the versatility of the equipment.

[0012] Preferably, two telescopic rods are rotatably connected to one end surface of the adjusting plate. The bottom ends of the two telescopic rods are rotatably connected to the bottom end of the inner wall of the positioning frame. A second spring is sleeved on the arc surface of each telescopic rod. The two ends of the second spring are fixedly connected to the fixed end and the moving end of the telescopic rod, respectively. A first coil spring is sleeved on the arc surface of one end of the auxiliary shaft. The two ends of the first coil spring are fixedly connected to the connecting frame and the positioning frame, respectively. The effect achieved by the above components is that the combined action of the telescopic rods, the second spring, and the first coil spring enables the connecting frame to automatically reset or maintain a preset angle after rotation, while providing continuous elastic clamping force to prevent the connecting frame from loosening due to vibration. The separation of the chuck and the adjusting column needs to overcome the spring force, ensuring the reliability of the locking state and the feel of operation.

[0013] Preferably, the docking device includes a docking ring, the inner wall of which is fixedly connected to the arc surface of the hydrogen tank. A collar is fixedly connected to the surface of the rotating frame, the inner wall of which is slidably inserted into the arc surface of the hydrogen tank. Several docking brackets are fixedly connected to the arc surface of the collar, an adjusting rod is rotatably connected to the inner wall of each docking bracket, and several limiting brackets are fixedly connected to the arc surface of the docking ring. The limiting brackets have a U-shaped cross-section, and their inner walls engage with the arc surface of the adjusting rods. An adjusting shaft is threadedly connected to the arc surface of one end of the adjusting rod. The above components achieve the following effects: the docking device, through the cooperation of the docking ring, collar, adjusting rod, and limiting brackets, enables rapid engagement between the hydrogen tank and the rotating frame; the engaging structure of the adjusting rod and limiting brackets prevents axial movement of the hydrogen tank; and the threaded locking of the adjusting shaft further enhances the connection strength, ensuring the hydrogen tank remains secure during UAV flight or refueling.

[0014] Preferably, the arc surface of the adjusting rod is slidably connected to a fixing frame, and fixing holes are provided on both sides of the surface of the limiting frame. The inner wall of the fixing hole is inserted into the arc surface of both ends of the fixing frame. The effect achieved by the above components is that the insertion structure of the fixing frame and the fixing hole can achieve secondary locking of the adjusting rod, preventing the adjusting rod from coming out of the limiting frame due to vibration; at the same time, the insertion design at both ends of the fixing frame facilitates quick unlocking, improving the convenience of loading and unloading hydrogen tanks.

[0015] Preferably, a second coil spring is fitted at both ends of the inner wall of the docking frame, and the two ends of the second coil spring are fixedly connected to the adjusting rod and the docking frame, respectively. The effect achieved by the above components is that the second coil spring allows the adjusting rod to automatically spring back to its initial position when no external force is applied, maintaining the engagement with the limiting frame and preventing the adjusting rod from accidentally disengaging; at the same time, the second coil spring provides a continuous elastic preload, reducing the sway gap of the adjusting rod and improving the vibration resistance of the docking device.

[0016] Compared with the prior art, the advantages and positive effects of the present invention are as follows: 1. In this invention, by setting up an adjustment device, the hydrogen tank can achieve smooth and precise linear movement under the drive of a servo motor and synchronous belt transmission. The rotating frame and support frame abut against the end of the hydrogen tank, ensuring the positional accuracy and structural stability of the hydrogen tank during docking or separation. Simultaneously, the cooperation between the guide rod and the guide groove restricts the freedom of the moving frame, preventing deflection and jamming; the first spring and the protective ring provide buffering at extreme positions, reducing impact and noise, and extending the service life of the device. This adjustment device is lightweight and has high transmission efficiency, effectively solving the problems of difficult manual adjustment and inaccurate positioning of hydrogen tanks during refueling of existing hydrogen-powered drones, thus improving automation and reliability.

[0017] 2. In this invention, by setting up a positioning device and utilizing the plug-in structure of the positioning frame, connecting frame, and positioning block in conjunction with the threaded locking of the positioning shaft, rapid assembly and disassembly and stable fixation between the UAV support frame and the power replenishment platform or body can be achieved. Simultaneously, the connecting frame can switch and lock between two working angles to adapt to different power replenishment posture requirements. The elastic action of the telescopic rod, the second spring, and the first coil spring ensures that the connecting frame automatically resets or maintains a preset angle after rotation, preventing loosening due to vibration. This positioning device significantly simplifies the installation process of the power replenishment equipment, improves the flexibility of angle adjustment and the reliability of locking, and overcomes the problems of simple fixing structures, easy loosening, and poor adaptability in existing technologies.

[0018] 3. In this invention, a docking device is used, employing a locking structure of the docking ring, collar, adjusting rod, and limiting frame, combined with the threaded locking of the adjusting shaft, to achieve a quick and secure connection between the hydrogen tank and the rotating frame. The secondary insertion structure of the fixing frame and fixing hole further prevents the adjusting rod from disengaging in a vibration environment, ensuring the safety of the hydrogen tank during UAV flight or refueling. The internal coil spring of the docking frame allows the adjusting rod to automatically spring back and engage with the limiting frame when no external force is applied, preventing accidental loosening and providing continuous pre-tightening force to reduce gap wobble. This docking device solves the problems of cumbersome operation, poor vibration resistance, and easy leakage in traditional hydrogen tank connection methods, improving refueling efficiency and flight safety. Attached Figure Description

[0019] Figure 1 This invention presents a three-dimensional structural schematic diagram of a lightweight hydrogen-powered drone refueling device; Figure 2 This invention provides a schematic diagram of the structure of an adjustment device for a lightweight hydrogen-powered drone refueling equipment. Figure 3 This invention provides a partial structural schematic diagram of an adjustment device for a lightweight hydrogen-powered drone refueling equipment. Figure 4 This invention provides an enlarged structural schematic diagram of point A of a lightweight hydrogen-powered drone refueling device; Figure 5 This invention presents a schematic diagram of the positioning device for a lightweight hydrogen-powered drone refueling equipment. Figure 6 This invention provides a partial structural schematic diagram of a positioning device for a lightweight hydrogen-powered drone refueling equipment. Figure 7 This invention presents an enlarged structural schematic diagram of section B of a lightweight hydrogen-powered drone refueling device; Figure 8 This invention presents a schematic diagram of the docking device for a lightweight hydrogen-powered drone refueling equipment.

[0020] Legend: 1. UAV body; 2. Fan blade frame; 3. Support frame; 4. Mounting frame; 5. Hydrogen tank; 6. Adjustment device; 601. Servo motor; 602. First synchronous pulley; 603. Synchronous belt; 604. Fixed frame; 605. Drive shaft; 606. Second synchronous pulley; 607. Moving frame; 608. Guide rod; 609. Guide groove; 610. Rotating frame; 611. Bearing frame; 612. Transmission frame; 613. Fixed roller; 614. First spring; 615. Protective ring; 7. Positioning device; 701. Positioning frame; 70 2. Positioning plate; 703. Connecting frame; 704. Positioning block; 705. Positioning shaft; 706. Auxiliary shaft; 707. Chuck; 708. Slot; 709. First coil spring; 710. Slide groove; 711. Adjusting plate; 712. Adjusting column; 713. Inlay hole; 714. Inlay column; 715. Telescopic rod; 716. Second spring; 8. Docking device; 81. Docking ring; 82. Limiting frame; 83. Collar; 84. Docking frame; 85. Second coil spring; 86. Adjusting rod; 87. Fixing frame; 88. Adjusting shaft; 89. Fixing hole. Detailed Implementation

[0021] 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.

[0022] 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.

[0023] like Figure 1-8As shown, the present invention provides a lightweight hydrogen-powered drone refueling device, including a drone body 1 and a docking device 8. A support frame 3 is provided at the bottom of the drone body 1. A mounting frame 4 is provided on the support frame 3 at the position corresponding to the upper surface of the drone body 1. A hydrogen tank 5 is provided at the upper end of the mounting frame 4. An adjustment device 6 is provided on the upper surface of the mounting frame 4. Fan blade frames 2 are installed on all four sides of the upper end of the drone body 1. A positioning device 7 is provided on the surface of the support frame 3 at the position corresponding to the bottom of the mounting frame 4.

[0024] The specific settings and functions of its adjustment device 6, positioning device 7, and docking device 8 will be described in detail below.

[0025] like Figure 2 , Figure 3 and Figure 4As shown, the adjustment device 6 includes two fixed frames 604 and a synchronous belt 603. The lower surfaces of the two fixed frames 604 are fixedly connected to both sides of the surface of the mounting frame 4. The inner wall of the fixed frame 604 is rotatably connected to a drive shaft 605. One end of the drive shaft 605 is fixedly connected to a second synchronous pulley 606. The surface of the mounting frame 4 is fixedly connected to a servo motor 601. The output end of the servo motor 601 is fixedly connected to two first synchronous pulleys 602. The two first synchronous pulleys 602 are connected to the second synchronous pulleys 606 via the synchronous belt 603. The arc surface of the drive shaft 605 is threadedly connected to a movable frame 607. The upper ends of the two movable frames 607 are rotatably connected to the same rotating frame 610. The inner wall of the rotating frame 610 is fixedly connected to the hydrogen tank 5 via a docking device 8. One side surface of the rotating frame 610 is fixedly connected to a support frame 611. The inner wall of the support frame 611 abuts against one end of the hydrogen tank 5. The adjustment device 6 is driven by a servo motor 601 and a synchronous belt 603, enabling the smooth movement of the moving frame 607 and the rotating frame 610. This allows for precise adjustment of the position of the hydrogen tank 5, facilitating docking or separation from the UAV body 1. Simultaneously, the support frame 611 provides abutment support to the end of the hydrogen tank 5, improving its stability and safety during movement and docking. The overall structure is lightweight, facilitating integration into the UAV's power replenishment system. Rotating frames are rotatably connected to both sides of the rotating frame 610, with an "L"-shaped cross-section. A fixed roller 613 is fixedly connected to one end of the mounting frame 4, and both ends of the fixed roller 613 are rotatably connected to the transmission frame 612. By setting up the L-shaped rotating frame and the transmission frame 612 rotatably connected to the fixed roller 613, the rotating frame 610 obtains stable rotational support during movement and angle changes, preventing the hydrogen tank 5 from shaking. Furthermore, the cooperation between the transmission frame 612 and the fixed roller 613 enhances the motion synchronization and structural strength of the rotating frame 610 during adjustment. A first spring 614 is slidably connected to one end of the drive shaft 605 via its arc surface. One end of the first spring 614 is fixedly connected to the inner wall surface of the fixed frame 604, and a protective ring 615 is fixedly connected to the other end of the first spring 614. The first spring 614 and the protective ring 615 on the drive shaft 605 provide buffer protection when the moving frame 607 moves to its limit position, reducing impact noise and component wear, extending the service life of the drive shaft 605 and the fixed frame 604, and preventing damage to the moving frame 607 due to overtravel. Guide rods 608 are fixedly connected to both sides of the moving frame 607. A guide groove 609 is formed on the side wall surface of the fixed frame 604, and the inner wall of the guide groove 609 is slidably connected to the arc surface of the guide rod 608. The sliding fit between the guide rod 608 and the guide groove 609 provides precise linear motion guidance for the moving frame 607, preventing the moving frame 607 from deflecting or getting stuck during movement, ensuring the repeatability of the hydrogen tank 5 docking position, and improving the operational reliability of the adjustment device 6.

[0026] like Figure 5 , Figure 6 and Figure 7As shown, the positioning device 7 includes two positioning frames 701. The cross-section of the positioning frame 701 is U-shaped. The two positioning frames 701 are located on both sides of the bottom end of the support frame 3. The inner wall of the positioning frame 701 is fixedly connected to the surface of the support frame 3. A connecting frame 703 is rotatably connected to one side of the inner wall of the positioning frame 701. The cross-section of the connecting frame 703 is L-shaped. Positioning plates 702 are fixedly connected to both sides of the bottom end of the support frame 3. Positioning blocks 704 are fixedly connected to the surface of the positioning plates 702. The surface of the positioning blocks 704 is inserted into the upper inner wall of the connecting frame 703. A positioning shaft 705 is threaded through the upper surface of the connecting frame 703. The bottom arc surface of the positioning shaft 705 is threaded through the surface of the positioning block 704. The positioning device 7, through the interlocking of the positioning frame 701, connecting frame 703, and positioning block 704, and the threaded locking using the positioning shaft 705, can quickly fix the support frame 3 to the UAV body 1 or external platform, achieving stable installation of the refueling equipment. The interlocking structure of the L-shaped connecting frame 703 and the positioning block 704 facilitates disassembly and assembly, improving the efficiency of equipment maintenance and hydrogen tank 5 replacement. The inner wall of the positioning frame 701 is provided with an adjusting plate 711, and the two ends of the adjusting plate 711 are respectively fixedly connected to adjusting columns 712 and embedded columns 714. The side wall surface of the positioning frame 701 has openings corresponding to the positions of the adjusting columns 712. The slide groove 710 and the positioning frame 701 have inlay holes 713 on their side wall surfaces corresponding to the inlay post 714. The inner wall of the inlay hole 713 is slidably connected to the arc surface of the inlay post 714. The inner wall of the slide groove 710 is slidably connected to the arc surface of the adjusting post 712. An auxiliary shaft 706 is fixedly connected to the bottom inner wall of the connecting frame 703. A chuck 707 is fixedly connected to the arc surface of the auxiliary shaft 706. Two slots 708 are opened on the surface of the chuck 707. The two slots 708 are distributed at a 90° angle on the surface of the chuck 707. The inner wall of one of the slots 708 is engaged with the arc surface of the adjusting post 712. Through the cooperation of the adjusting plate 711, adjusting column 712, inlaid column 714, and 90° included angle slot 708 on the chuck 707, the connecting frame 703 can switch and lock between two working angles. The snap-fit ​​structure between the adjusting column 712 and the slot 708 ensures the stability after angle switching, thereby adapting to the energy replenishment operation requirements under different postures and enhancing the versatility of the equipment. Two telescopic rods 715 are rotatably connected to one end surface of the adjusting plate 711. The bottom ends of the two telescopic rods 715 are rotatably connected to the bottom end of the inner wall of the positioning frame 701. The arc surface of the telescopic rod 715 is fitted with a second spring 716. The two ends of the second spring 716 are fixedly connected to the fixed end and the moving end of the telescopic rod 715, respectively. The arc surface of one end of the auxiliary shaft 706 is fitted with a first coil spring 709. The two ends of the first coil spring 709 are fixedly connected to the connecting frame 703 and the positioning frame 701, respectively.The combined action of the telescopic rod 715, the second spring 716, and the first coil spring 709 enables the connecting frame 703 to automatically reset or maintain a preset angle after rotation, while providing continuous elastic clamping force to prevent the connecting frame 703 from loosening due to vibration; the separation of the chuck 707 from the adjusting column 712 requires overcoming the spring force, ensuring the reliability of the locking state and the feel of operation.

[0027] like Figure 8 As shown, the docking device 8 includes a docking ring 81, the inner wall of which is fixedly connected to the arc surface of the hydrogen tank 5. A collar 83 is fixedly connected to the surface of the rotating frame 610. The inner wall of the collar 83 is slidably inserted into the arc surface of the hydrogen tank 5. Several docking frames 84 are fixedly connected to the arc surface of the collar 83. An adjusting rod 86 is rotatably connected to the inner wall of the docking frame 84. Several limiting frames 82 are fixedly connected to the arc surface of the docking ring 81. The cross-section of the limiting frame 82 is U-shaped. The inner wall of the limiting frame 82 is engaged with the arc surface of the adjusting rod 86. An adjusting shaft 88 is threadedly connected to the arc surface of one end of the adjusting rod 86. The docking device 8 achieves rapid engagement between the hydrogen tank 5 and the rotating frame 610 through the cooperation of the docking ring 81, collar 83, adjusting rod 86 and limiting frame 82. The engagement structure of the adjusting rod 86 and the limiting frame 82 can prevent the hydrogen tank 5 from moving axially, while the threaded locking of the adjusting shaft 88 further enhances the connection strength, keeping the hydrogen tank 5 firmly in place during UAV flight or refueling. The arc surface of the adjusting rod 86 is slidably connected to the fixing frame 87. The limiting frame 82 has fixing holes 89 on both sides of its surface, and the inner wall of the fixing hole 89 is inserted into the arc surface of both ends of the fixing frame 87. The insertion structure of the fixing bracket 87 and the fixing hole 89 allows for secondary locking of the adjusting rod 86, preventing it from dislodging from the limiting bracket 82 due to vibration. Simultaneously, the insertion design at both ends of the fixing bracket 87 facilitates quick unlocking, improving the ease of loading and unloading the hydrogen tank 5. Both ends of the inner wall of the docking bracket 84 are fitted with second coil springs 85, with each end of the second coil spring 85 fixedly connected to the adjusting rod 86 and the docking bracket 84, respectively. The second coil springs 85 allow the adjusting rod 86 to automatically spring back to its initial position when no external force is applied, maintaining its engagement with the limiting bracket 82 and preventing accidental disengagement. Furthermore, the second coil springs 85 provide continuous elastic preload, reducing the swaying gap of the adjusting rod 86 and improving the vibration resistance of the docking device 8.

[0028] The overall working principle is as follows: the entire lightweight hydrogen-powered drone refueling equipment mainly consists of the drone body 1, support frame 3, mounting frame 4, and adjustment device 6, docking device 8, and positioning device 7 set on the mounting frame 4. During operation, the hydrogen tank 5 is first reliably fixed to the rotating frame 610 through the docking device 8: the hydrogen tank 5 is inserted into the collar 83, so that the docking ring 81 abuts against the rotating frame 610. Then, the adjustment rod 86 is rotated to lock into the limiting frame 82, and the adjustment shaft 88 is tightened to lock the threads. If necessary, the fixing frame 87 is inserted for secondary locking. The second coil spring 85 ensures that the adjustment rod 86 is always in the locked state, thereby quickly completing the installation of the hydrogen tank 5.

[0029] Subsequently, the servo motor 601 in the adjustment device 6 is activated. The output of the servo motor 601 drives the two first synchronous pulleys 602 to rotate, which in turn drives the second synchronous pulley 606 and the drive shaft 605 to rotate via the synchronous belt 603. The drive shaft 605 is threadedly engaged with the moving frame 607. Guided by the guide rod 608 and the guide groove 609, the moving frame 607 moves linearly along the fixed frame 604. The two moving frames 607 move synchronously, driving the upper rotating frame 610 and the hydrogen tank 5 inside to move smoothly, achieving precise docking or disengagement of the hydrogen tank 5 with the hydrogen interface on the UAV body 1. During the movement, the support frame 611 always abuts against the end of the hydrogen tank 5 to maintain stability; the first spring 614 and the protective ring 615 at the end of the drive shaft 605 provide buffering at the extreme positions to prevent overtravel impact.

[0030] When the recharging angle needs to be adjusted or different ground attitudes need to be adapted, the relative angle between the support frame 3 and the UAV body 1 is adjusted via the positioning device 7. The connecting frame 703 is rotated up or down, causing the positioning block 704 at the upper end of the connecting frame 703 to engage or disengage with the positioning block 704 on the positioning plate 702, and then locked via the positioning shaft 705. Simultaneously, the adjusting column 712 on the adjusting plate 711 switches between the two 90° angled slots 708 of the chuck 707, achieving locking of the connecting frame 703 at two different working angles. The telescopic rod 715, the second spring 716, and the first coil spring 709 provide elastic restoring force and continuous preload, ensuring stable positioning after angle switching and preventing loosening due to vibration.

[0031] Throughout the process, support frame 3 is fixed to the bottom of the UAV body 1, mounting frame 4 is positioned above support frame 3, hydrogen tank 5 is fixed to rotating frame 610 via docking device 8, and linear displacement for energy replenishment is achieved via adjustment device 6. Positioning device 7 ensures stable and reliable connection between the entire system and the external platform or the UAV itself. The coordinated operation of these devices enables rapid assembly and disassembly, precise positioning, angle adjustment, and safe docking of hydrogen tank 5, thereby completing the efficient hydrogen refueling task.

[0032] 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. A lightweight hydrogen-powered drone refueling device, comprising a drone body (1) and a docking device (8), characterized in that: The bottom of the UAV body (1) is provided with a support frame (3). The support frame (3) is provided with a mounting frame (4) at the position of the upper surface of the UAV body (1). The upper end of the mounting frame (4) is provided with a hydrogen tank. The upper surface of the mounting frame (4) is provided with an adjustment device (6). The upper four sides of the UAV body (1) are all equipped with fan blade frames (2). The adjustment device (6) includes two fixed frames (604) and a synchronous belt (603). The lower surfaces of the two fixed frames (604) are fixedly connected to the two sides of the surface of the mounting frame (4). The inner wall of the fixed frame (604) is rotatably connected to a drive shaft (605). One end of the drive shaft (605) is fixedly connected to a second synchronous wheel (606). A servo motor (601) is fixedly connected to the surface of the mounting bracket (4). Two first synchronous pulleys (602) are fixedly connected to the output end of the servo motor (601). The two first synchronous pulleys (602) are connected to the second synchronous pulley (606) via a synchronous belt (603). A movable frame (607) is threadedly connected to the arc surface of the drive shaft (605). The upper ends of the two movable frames (607) are rotatably connected to the same rotating frame (610). The inner wall of the rotating frame (610) is fixedly connected to the hydrogen tank (5) via a docking device (8). A support frame (611) is fixedly connected to one side surface of the rotating frame (610). The inner wall of the support frame (611) abuts against one end of the hydrogen tank (5).

2. The lightweight hydrogen-powered drone refueling device according to claim 1, characterized in that: The rotating frame (610) has rotating brackets rotatably connected to both sides of its rotating frame. The rotating brackets have an "L" shaped cross section. A fixed roller (613) is fixedly connected to one end of the mounting frame (4). The two ends of the fixed roller (613) are rotatably connected to the transmission frame (612).

3. The lightweight hydrogen-powered drone refueling device according to claim 1, characterized in that: One end of the drive shaft (605) is slidably connected to a first spring (614) on an arc surface. One end of the first spring (614) is fixedly connected to the inner wall surface of the fixed frame (604), and the other end of the first spring (614) is fixedly connected to a protective ring (615).

4. The lightweight hydrogen-powered drone refueling device according to claim 1, characterized in that: Guide rods (608) are fixedly connected to both sides of the movable frame (607), and guide grooves (609) are provided on the side wall surface of the fixed frame (604). The inner wall of the guide groove (609) is slidably connected to the arc surface of the guide rod (608).

5. A lightweight hydrogen-powered drone refueling device according to claim 1, wherein a positioning device (7) is provided on the surface of the support frame (3) at the position corresponding to the bottom end of the mounting frame (4), the positioning device (7) includes two positioning frames (701), the cross-section of the positioning frame (701) is "U" shaped, the two positioning frames (701) are respectively located on both sides of the bottom end of the support frame (3), the inner wall of the positioning frame (701) is fixedly connected to the surface of the support frame (3), and one side of the inner wall of the positioning frame (701) is rotatably connected. There is a connecting frame (703), the cross section of the connecting frame (703) is "L" shaped, and the bottom two sides of the support frame (3) are fixedly connected to positioning plates (702). The surface of the positioning plate (702) is fixedly connected to a positioning block (704). The surface of the positioning block (704) is inserted into the upper inner wall of the connecting frame (703). The upper surface of the connecting frame (703) is threaded through a positioning shaft (705), and the bottom arc surface of the positioning shaft (705) is threaded through the surface of the positioning block (704).

6. A lightweight hydrogen-powered drone refueling device according to claim 5, characterized in that: The inner wall of the positioning frame (701) is provided with an adjusting plate (711). An adjusting column (712) and an inlay column (714) are fixedly connected to both ends of the adjusting plate (711). A sliding groove (710) is provided on the side wall surface of the positioning frame (701) corresponding to the position of the adjusting column (712). An inlay hole (713) is provided on the side wall surface of the positioning frame (701) corresponding to the position of the inlay column (714). The inner wall of the inlay hole (713) is slidably connected to the arc surface of the inlay column (714). The inner wall of the slide groove (710) is slidably connected to the arc surface of the adjusting column (712). An auxiliary shaft (706) is fixedly connected to the inner wall of the bottom end of the connecting frame (703). A chuck (707) is fixedly connected to the arc surface of the auxiliary shaft (706). Two slots (708) are opened on the surface of the chuck (707). The two slots (708) are distributed at a 90° angle on the surface of the chuck (707). The inner wall of one of the slots (708) is engaged with the arc surface of the adjusting column (712).

7. A lightweight hydrogen-powered drone refueling device according to claim 6, characterized in that: Two telescopic rods (715) are rotatably connected to one end surface of the adjusting plate (711). The bottom ends of the two telescopic rods (715) are rotatably connected to the bottom end of the inner wall of the positioning frame (701). A second spring (716) is sleeved on the arc surface of the telescopic rod (715). The two ends of the second spring (716) are fixedly connected to the fixed end and the moving end of the telescopic rod (715) respectively. A first coil spring (709) is sleeved on the arc surface of one end of the auxiliary shaft (706). The two ends of the first coil spring (709) are fixedly connected to the connecting frame (703) and the positioning frame (701) respectively.

8. A lightweight hydrogen-powered drone refueling device according to claim 1, characterized in that: The docking device (8) includes a docking ring (81), the inner wall of which is fixedly connected to the arc surface of the hydrogen tank (5), a collar (83) is fixedly connected to the surface of the rotating frame (610), the inner wall of which is slidably inserted into the arc surface of the hydrogen tank (5), a plurality of docking frames (84) are fixedly connected to the arc surface of the collar (83), an adjusting rod (86) is rotatably connected to the inner wall of the docking frame (84), a plurality of limiting frames (82) are fixedly connected to the arc surface of the docking ring (81), the cross section of the limiting frame (82) is "U" shaped, the inner wall of the limiting frame (82) is engaged with the arc surface of the adjusting rod (86), and an adjusting shaft (88) is threadedly connected to the arc surface of one end of the adjusting rod (86).

9. A lightweight hydrogen-powered drone refueling device according to claim 1, characterized in that: The adjusting rod (86) is slidably connected to the fixing frame (87) on its arc surface. The limiting frame (82) has fixing holes (89) on both sides of its surface. The inner wall of the fixing hole (89) is inserted into the arc surface of both ends of the fixing frame (87).

10. A lightweight hydrogen-powered drone refueling device according to claim 8, characterized in that: The inner walls of the docking frame (84) are fitted with second coil springs (85) at both ends, and the two ends of the second coil springs (85) are fixedly connected to the adjusting rod (86) and the docking frame (84) respectively.

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