An unmanned aerial vehicle with hydrogen storage bottle quick change support

Abstract

This invention relates to the field of hydrogen fuel cell drone technology, specifically to a drone with a quick-change support for hydrogen storage cylinders, comprising a rotating groove and a sliding groove; further comprising: multiple support sleeves, each corresponding to one of the vertical structures, the support sleeves being rotatably mounted on one side of the vertical structure; a rotating component connected to the support sleeves and extending into the rotating groove, the outer periphery of the rotating component having two curved surfaces that can simultaneously slide against the inner wall of the rotating groove, the centers of the two curved surfaces coinciding and the maximum distance between the two curved surfaces being the same as the diameter of the rotating groove; the outer periphery of the rotating component also includes two parallel planes, the straight-line distance between the two planes being the same as the width of the sliding groove; and a lifting unit located at the bottom of the drone fuselage, used to simultaneously drive all the support sleeves to lift and lower. This invention improves the ease of assembly and disassembly of hydrogen cylinders.

Description

Technical Field

[0001] This invention relates to the field of hydrogen fuel cell drone technology, specifically to a drone with a quick-change support for hydrogen storage tanks. Background Technology

[0002] Depending on the usage requirements and design structure, hydrogen fuel cell drones have different layouts for hydrogen cylinders. Some hydrogen cylinders are horizontally placed at the bottom of the drone, some are horizontally placed at the top, and some are vertically placed at the feet.

[0003] Chinese Patent Publication No. CN119099864A discloses a positioning device for a hydrogen cylinder of a hydrogen fuel cell drone, including a bottom support plate, a rotor bracket, a top support plate, a hydrogen fuel cell, a controller, a lifting rotor, support legs, an extension seat, a hydrogen cylinder bracket, a hydrogen cylinder, a gas guide pipe, a camera bracket, and a gas guide structure. The rotor bracket is fixedly installed on the surface of the bottom support plate, and the top support plate is fixedly installed above the rotor bracket. The hydrogen fuel cell is fixedly installed in the middle of the surface of the bottom support plate, and the controller is fixedly installed on the surface of the top support plate. The lifting rotor is fixedly installed on the top of the rotor bracket. The support legs are fixedly installed at the bottom of the bottom support plate, and the extension seat is fixedly installed on the inner side of the support legs. The hydrogen cylinder bracket is fixedly installed on the inner side of the support legs. The hydrogen cylinder is installed inside the hydrogen cylinder bracket, and the gas guide structure is fixedly installed at the middle position of the bottom of the bottom support plate. The hydrogen cylinder is connected to the gas guide structure through the gas guide pipe. The camera bracket is fixedly installed at both ends of the bottom of the bottom support plate.

[0004] The above solution vertically positions the hydrogen cylinders at the feet of the hydrogen fuel cell drone, dividing the traditional single hydrogen cylinder into multiple cylinders to supply hydrogen to the fuel cell, thus improving safety. However, because the hydrogen cylinders are vertically positioned, they can only be replaced by rotating and tilting during disassembly and replacement. Otherwise, the hydrogen cylinders will be blocked by the drone's body and cannot be removed. Therefore, a support frame for supporting the hydrogen cylinders needs to be hinged to each foot. Each support frame has a limiting mechanism at its upper part. When replacing the hydrogen cylinders, the limiting mechanism needs to be unlocked, making the replacement process slow. Furthermore, since the limiting mechanism needs to be manually operated to limit the hydrogen cylinders after installation, if an error occurs during the limiting process, some hydrogen cylinders may not be stably limited. If the limiting mechanism accidentally comes loose during drone flight, it will not only cause the hydrogen cylinders to fall and damage the pipeline between the hydrogen cylinders and the fuel cell, but it will also change the drone's original stability, causing unstable flight and potentially leading to a safety accident. Summary of the Invention

[0005] To address the aforementioned issues, a drone with a quick-change hydrogen storage cylinder support is provided. Through the cooperation of the support sleeve and the rotating component, the interconnected design of the rotating groove and the sliding groove, and the synchronous driving action of the lifting unit, the technical problems of slow hydrogen cylinder installation and removal and unstable positioning in existing hydrogen fuel cell drones are effectively solved. It eliminates the need for additional hinged support frames and multiple limiting mechanisms, and eliminates the need for manual one-by-one positioning, significantly accelerating the installation and removal speed of hydrogen cylinders and reducing the difficulty of operation. At the same time, it enables the simultaneous installation and removal of multiple hydrogen cylinders, in conjunction with the cooperation of the rotating component and the sliding groove, and the contact and positioning of the hydrogen cylinders with the support legs.

[0006] To address the problems of existing technologies, the present invention provides a drone with a quick-change support for hydrogen storage cylinders, comprising a drone fuselage and legs, wherein the legs have multiple vertical structures, and a hydrogen cylinder body is respectively provided on one side of each of the multiple vertical structures; The vertical structure has a rotating groove, which is circular. A sliding groove is vertically formed at the top of the rotating groove, and the sliding groove is connected to the rotating groove. The diameter of the rotating groove is greater than the width of the sliding groove. The drone also includes: Multiple support sleeves are provided, each corresponding to one of the vertical structures, and the support sleeves are rotatably mounted on one side of the vertical structure; A rotating component is connected to the support sleeve and extends into the rotating groove. The outer periphery of the rotating component has two curved surfaces that can simultaneously slide against the inner wall of the rotating groove. The centers of the two curved surfaces coincide and the maximum distance between the two curved surfaces is the same as the diameter of the rotating groove. The outer periphery of the rotating component also includes two parallel planes. The two curved surfaces are connected by the two planes, and the straight-line distance between the two planes is the same as the width of the sliding groove. A lifting unit is located at the bottom of the drone fuselage and is used to simultaneously drive all the support sleeves to lift.

[0007] Preferably, the connection point between the rotating component and the support sleeve is located in the upper half of the support sleeve.

[0008] Preferably, the side of the hydrogen cylinder body is provided with a connector, and the upper part of the support sleeve is provided with a snap-fit, which engages with the connector.

[0009] Preferably, the lifting unit includes: The lifting frame is vertically movable and disposed at the lower part of the UAV fuselage, and the lifting frame is hinged to the support sleeve; A drive unit is disposed between the lifting frame and the drone fuselage for driving the lifting frame to move.

[0010] Preferably, the driving unit includes: A rotary actuator is located at the lower part of the drone fuselage; A lead screw is vertically fixed on the output end of the rotary driver, and the lead screw passes through the lifting frame and is threadedly engaged with the lifting frame.

[0011] Preferably, a limiting block is fixedly provided at the bottom of the lead screw, and the maximum length of the limiting block on the horizontal plane is greater than the diameter of the lead screw.

[0012] Preferably, the bottom of the drone fuselage is vertically provided with multiple limiting rods that slide in cooperation with the lifting frame, the multiple limiting rods forming a limiting area, and the lifting frame moving up and down within the limiting area.

[0013] Preferably, a detection block is fixedly mounted on the lead screw, and a Hall sensor is mounted on one side of the detection block.

[0014] Preferably, the support sleeve is provided with a flame-retardant flocked layer.

[0015] The advantages of this invention compared to the prior art are: 1. This invention effectively solves the technical problems of slow hydrogen cylinder assembly and disassembly and unstable positioning in existing hydrogen fuel cell drones by using the cooperation between the support sleeve and the rotating component, the connection between the rotating groove and the sliding groove, and the synchronous driving action of the lifting unit. It eliminates the need for additional hinged support frames and multiple limiting mechanisms, and eliminates the need for manual one-by-one limiting, which greatly speeds up the assembly and disassembly of hydrogen cylinders and reduces the difficulty of operation. At the same time, it enables the simultaneous installation and disassembly of multiple hydrogen cylinders. With the cooperation between the rotating component and the sliding groove and the contact limiting between the hydrogen cylinder and the support leg, it ensures the stability of the hydrogen cylinder positioning, prevents it from falling and pulling on the pipeline, and improves the flight safety of the drone.

[0016] 2. By connecting the rotating part to the upper part of the support sleeve and the snap-fit ​​design of the connector and the bayonet, the installation process of the hydrogen cylinder is further optimized, and the circumferential limit of the hydrogen cylinder is realized to prevent it from rotating in the support sleeve. This ensures the stable connection between the gas supply pipe and the connector and avoids gas leakage. Without increasing the difficulty of operation and manufacturing cost, the efficiency of disassembly and assembly and the reliability of the limit are further improved.

[0017] 3. Through the specific structural design of the lifting unit and the redundant detection structure, the overall stability and safety of the device are improved. The cooperation between the lead screw and the rotary drive enables the lifting frame to rise and fall accurately and smoothly. The limit block and the limit rod respectively realize the limit and guide of the lifting frame to prevent it from falling excessively or tilting. The cooperation between the detection block and the Hall sensor realizes the real-time detection of the limit status, timely detection of abnormalities and triggering the protection mechanism to avoid safety accidents, improve the safety protection system and extend the service life of the device. Attached Figure Description

[0018] Figure 1This is a three-dimensional schematic diagram of a drone with a quick-change bracket for hydrogen storage cylinders according to the present invention.

[0019] Figure 2 This invention relates to a drone with a quick-change bracket for hydrogen storage cylinders. Figure 1 A magnified view of a portion of point A in the middle.

[0020] Figure 3 This is a three-dimensional schematic diagram of a drone with a quick-change bracket for hydrogen storage cylinders during the replacement of hydrogen cylinders, according to the present invention.

[0021] Figure 4 This invention relates to a drone with a quick-change hydrogen storage tank bracket, which removes the three-dimensional diagram of the drone's rear fuselage. Figure 1 .

[0022] Figure 5 The present invention relates to a drone with a quick-change bracket for hydrogen storage cylinders, which removes the front view of the drone's rear fuselage.

[0023] Figure 6 This invention relates to a drone with a quick-change bracket for hydrogen storage cylinders. Figure 5 Schematic diagram of cross-section at point BB.

[0024] Figure 7 This is a cross-sectional perspective view of a drone with a quick-change bracket for hydrogen storage cylinders according to the present invention.

[0025] Figure 8 This invention relates to a drone with a quick-change bracket for hydrogen storage cylinders. Figure 7 A magnified view of a portion of point C.

[0026] Figure 9 This invention relates to a drone with a quick-change hydrogen storage tank bracket, which removes the three-dimensional diagram of the drone's rear fuselage. Figure 2 .

[0027] Figure 10 This is a three-dimensional schematic diagram of a drone with a quick-change hydrogen storage tank bracket according to the present invention, after removing the drone body and legs.

[0028] The following are the labels in the diagram: 1. UAV fuselage; 11. Limiting rod; 2. Support leg; 21. Rotating groove; 22. Sliding groove; 3. Hydrogen cylinder body; 31. Connector; 4. Support sleeve; 41. Rotating component; 42. Bayonet; 5. Lifting unit; 51. Lifting frame; 52. Drive unit; 521. Rotary actuator; 522. Lead screw; 523. Limiting block; 53. Detection block; 54. Hall sensor; 6. Gas supply pipe. Detailed Implementation

[0029] To further understand the features, technical means, and specific objectives and functions achieved by the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0030] Reference Figures 1 to 5 , Figure 9 and Figure 10 A drone with a quick-change support for a hydrogen storage cylinder includes a drone body 1 and legs 2. The legs 2 have multiple vertical structures, and a hydrogen cylinder body 3 is respectively provided on one side of each of the multiple vertical structures. The vertical structure is provided with a rotating groove 21, which is circular in shape. A sliding groove 22 is vertically provided on the upper part of the rotating groove 21. The sliding groove 22 is connected to the rotating groove 21, and the diameter of the rotating groove 21 is greater than the width of the sliding groove 22. The drone also includes: Multiple support sleeves 4 are provided, each corresponding to one of the number of vertical structures. Each support sleeve 4 is rotatably mounted on one side of the vertical structure. The rotating component 41 is connected to the support sleeve 4 and extends into the rotating groove 21. The outer periphery of the rotating component 41 has two curved surfaces that can simultaneously slide with the inner wall of the rotating groove 21. The centers of the two curved surfaces coincide and the maximum distance between the two curved surfaces is the same as the diameter of the rotating groove 21. The outer periphery of the rotating component 41 also includes two parallel planes. The two curved surfaces are connected by the two planes, and the straight-line distance between the two planes is the same as the width of the sliding groove 22. The lifting unit 5 is located at the bottom of the drone body 1 and is used to simultaneously drive all the support sleeves 4 to lift.

[0031] Multiple air supply pipes 6 are provided on the drone body 1. The air supply pipes 6 are fixedly connected to the drone body 1. The end of the air supply pipe 6 away from the drone body 1 is connected to the connector 31 provided on the hydrogen cylinder body 3.

[0032] In daily use, first insert the hydrogen cylinder body 3 into the corresponding support sleeve 4 from the top. During insertion, manually rotate the support sleeve 4 to ensure smooth insertion of the hydrogen cylinder body 3, while ensuring that the connector 31 on the hydrogen cylinder body 3 is aligned and connected to the end of the gas supply pipe 6 away from the drone body 1. When the support sleeve 4 rotates, the rotating component 41 connected to it rotates within the rotating groove 21 opened on the vertical structure, ensuring smooth rotation of the support sleeve 4. After all the gas supply pipes 6 are connected to the connector 31 on the corresponding hydrogen cylinder body 3, start the lifting unit 5, which drives all the support sleeves 4 to rise synchronously. During the rise, the rotating component 41 slides from the rotating groove 21 into the sliding groove 22 connected to it. Since the diameter of the rotating groove 21 is larger than the width of the sliding groove 22, and the straight-line distance between the two planes on the outer periphery of the rotating component 41 is the same as the width of the sliding groove 22, the rotating component 41 cannot rotate after entering the sliding groove 22, and can only slide along the extension direction of the sliding groove 22. When the support sleeve 4 rises to the preset position, the upper end of the hydrogen cylinder body 3 abuts against the upper part of the vertical structure of the support leg 2, thereby limiting the hydrogen cylinder body 3 and fixing it in place.

[0033] When the drone returns and lands due to insufficient fuel, the lifting unit 5 is activated, driving all support sleeves 4 to descend synchronously. When the support sleeves 4 descend to the preset position, the rotating part 41 slides completely back into the rotating groove 21, and the lifting unit 5 stops operating. The user disconnects the gas supply pipes 6 one by one from the connectors 31 of the corresponding hydrogen cylinder bodies 3, then manually rotates the support sleeves 4 to tilt them, pulling the hydrogen cylinder bodies 3 out of the support sleeves 4 and replacing them with new ones. After replacement, the tilted support sleeves 4 are released, and the support sleeves 4 can return to a vertical state with their own structural cooperation. Then, the gas supply pipes 6 are reconnected to the connectors 31 on the hydrogen cylinder bodies 3, the lifting unit 5 is activated, so that the upper part of the hydrogen cylinder body 3 set in the support sleeve 4 abuts against the upper part of the support leg 2, thus completing the replacement of the hydrogen cylinder body 3 and preparing it for the next use.

[0034] This design effectively solves the technical problems of slow disassembly and replacement of hydrogen cylinders in existing hydrogen fuel cell drones, insufficient stability in limiting positions, and the potential for safety accidents. Through the cooperation between the support sleeve 4 and the rotating component 41, and the connection between the rotating groove 21 and the sliding groove 22, the support sleeve 4 can rotate freely within the rotating groove 21 under the drive of the rotating component 41. This allows the user to rotate the support sleeve 4 to avoid obstruction by the drone body 1 when inserting the hydrogen cylinder body 3, eliminating the need for additional hinged support frames and multiple limiting mechanisms, thus simplifying the structure. It also eliminates the need for manual operation of each limiting mechanism to limit the hydrogen cylinder body 3, significantly accelerating the disassembly and replacement speed and reducing operational difficulty. The lifting unit 5 can simultaneously drive all support sleeves 4 to lift synchronously, enabling the simultaneous installation and removal of multiple hydrogen cylinder bodies 3. To further improve replacement efficiency, and during the lifting process, the rotating part 41 slides from the rotating groove 21 into the sliding groove 22 and cannot rotate, but can only slide along the sliding groove 22. In conjunction with the contact limit between the upper end of the hydrogen cylinder body 3 and the upper part of the support leg 2, the stable limit of the hydrogen cylinder body 3 is achieved, avoiding the errors that may occur with manual limit, preventing the hydrogen cylinder body 3 from accidentally falling and pulling the pipeline due to loose limit, ensuring the structural stability of the UAV during flight and reducing the risk of safety accidents; the overall structural design is simple and reasonable, without the need for additional complex limit components, reducing the manufacturing cost of the device while ensuring convenient disassembly and assembly and limit stability.

[0035] Reference Figures 1 to 10 The connection position between the rotating component 41 and the support sleeve 4 is located in the upper half of the support sleeve 4.

[0036] After the hydrogen cylinder body 3 is inserted into the support sleeve 4, the connection between the rotating part 41 and the support sleeve 4 is located in the upper part of the support sleeve 4, causing the center of gravity of the support sleeve 4 to shift downwards. Guided by its own center of gravity, the support sleeve 4 will naturally tend to be vertical, eliminating the need for manual adjustment by the user. This simplifies the reset operation after the hydrogen cylinder body 3 is installed and improves installation efficiency. Simultaneously, the vertical orientation of the support sleeve 4 under the influence of its center of gravity ensures that when the lifting unit 5 drives the support sleeve 4 upwards, the rotating part 41 can accurately align with the sliding groove 22 and slide smoothly in, guaranteeing the proper cooperation of the limiting structure. This further enhances the stability of the hydrogen cylinder body 3's limiting position and prevents the rotating part 41 from failing to smoothly enter the sliding groove 22 due to the tilt of the support sleeve 4, thus preventing the hydrogen cylinder body 3's limiting position from failing and ensuring the safety of the drone's flight. During the replacement of the hydrogen cylinder body 3, the support sleeve 4 can also quickly reset after tilting and being released, thanks to its own center of gravity and connection position, facilitating subsequent installation steps and further optimizing the disassembly and assembly process.

[0037] Reference Figure 3The hydrogen cylinder body 3 is provided with a connector 31 on its side, and the upper part of the support sleeve 4 is provided with a snap-fit ​​42, which engages with the connector 31.

[0038] When inserting the hydrogen cylinder body 3 from the top of the support sleeve 4, the connector 31 on the side of the hydrogen cylinder body 3 must be aligned with the latch 42 on the top of the support sleeve 4. After the hydrogen cylinder body 3 is fully inserted into the support sleeve 4, the connector 31 and the latch 42 engage, thereby restricting the rotation of the hydrogen cylinder body 3 within the support sleeve 4. This structure achieves circumferential positioning of the hydrogen cylinder body 3 without the need for additional limiting components, ensuring that the connection position between the gas supply pipe 6 and the connector 31 remains stable. This prevents the connector 31 from detaching from the gas supply pipe 6 or causing leakage due to the rotation of the hydrogen cylinder body 3 caused by vibration during drone flight, thus ensuring the stability of the hydrogen supply. Furthermore, the snap-fit ​​mechanism is simple in structure and convenient to operate. Circumferential positioning is achieved simultaneously with the insertion of the hydrogen cylinder body 3, without affecting the efficiency of assembly and disassembly. It can also cooperate with rotating parts 41, sliding grooves 22, and other structures to further enhance the overall positioning effect of the hydrogen cylinder body 3, preventing rotation or displacement and reducing safety hazards.

[0039] Reference Figure 4 The lifting unit 5 includes: The lifting frame 51 is vertically movable and disposed at the lower part of the UAV fuselage 1, and the lifting frame 51 is hinged to the support sleeve 4; A drive unit 52 is disposed between the lifting frame 51 and the UAV body 1, and is used to drive the lifting frame 51 to move.

[0040] The lifting unit 5 consists of a lifting frame 51 and a drive unit 52. The lifting frame 51 is vertically movable and located at the lower part of the drone fuselage 1, and is hinged to the support sleeve 4. The drive unit 52 is located between the lifting frame 51 and the drone fuselage 1, and is used to drive the lifting frame 51 to move. When installing the hydrogen cylinder body 3, the drive unit 52 is activated, driving the lifting frame 51 to rise vertically. Since the lifting frame 51 is hinged to all the support sleeves 4, it can drive all the support sleeves 4 to rise synchronously, ensuring that multiple hydrogen cylinder bodies 3 complete the limit operation at the same time, improving installation efficiency. The hinged connection can adapt to the angle change of the support sleeve 4 during rotation, avoiding jamming between the support sleeve 4 and the lifting frame 51, ensuring that the support sleeve 4 can rotate freely to facilitate the insertion of the hydrogen cylinder body 3, and can rise and fall smoothly under the drive of the lifting frame 51. When replacing the hydrogen cylinder body 3, the drive unit 52 drives the lifting frame 51 to descend, causing all the support sleeves 4 to descend synchronously. This allows the rotating component 41 to slide completely back into the rotating groove 21, facilitating the rotation and tilting of the support sleeves 4 for disassembly of the hydrogen cylinder body 3. This structure achieves synchronicity and stability in the lifting and lowering of the support sleeves 4, simplifies the control logic of the lifting unit 5, and improves the stability of the lifting operation. It also prevents the hydrogen cylinder body 3 from failing to limit due to abnormal lifting or lowering of a single support sleeve 4, ensuring the flight safety of the UAV.

[0041] Reference Figure 8 and Figure 10 The driving unit 52 includes: A rotary actuator 521 is disposed at the lower part of the UAV fuselage 1; A lead screw 522 is vertically fixed on the output end of the rotary driver 521. The lead screw 522 passes through the lifting frame 51 and is threadedly engaged with the lifting frame 51.

[0042] The drive unit 52 consists of a rotary driver 521 and a lead screw 522. The rotary driver 521 is located at the lower part of the UAV fuselage 1, and the lead screw 522 is vertically fixed to the output end of the rotary driver 521, passing through the lifting frame 51 and threadedly engaging with it. When the lifting frame 51 needs to be raised or lowered, the rotary driver 521 is activated, driving the lead screw 522 to rotate. Due to the threaded engagement between the lead screw 522 and the lifting frame 51, the rotational motion of the lead screw 522 is converted into the vertical linear motion of the lifting frame 51, achieving smooth raising and lowering of the lifting frame 51. The threaded engagement method features high transmission accuracy and strong stability, allowing precise control of the lifting height of the lifting frame 51, ensuring that all support sleeves 4 rise and fall synchronously to the preset position, and ensuring that the upper end of the hydrogen cylinder body 3 precisely abuts against the upper part of the vertical structure of the support leg 2, guaranteeing the limiting effect. Meanwhile, the threaded drive has a self-locking function. After the lifting frame 51 rises to the preset position, no additional locking components are needed to keep the lifting frame 51 stable, preventing vibrations during the drone's flight from causing the lifting frame 51 to descend. This also prevents the hydrogen cylinder body 3 from loosening, improving the safety and stability of the device. This drive structure is simple, reliable, and can accurately match the lifting requirements of the support sleeve 4, further optimizing the working performance of the lifting unit 5.

[0043] Reference Figure 8 A limiting block 523 is fixedly provided at the bottom of the lead screw 522, and the maximum length of the limiting block 523 on the horizontal plane is greater than the diameter of the lead screw 522.

[0044] A limiting block 523 is fixedly installed at the bottom of the lead screw 522, and the maximum length of the limiting block 523 on the horizontal plane is greater than the diameter of the lead screw 522. When the lifting frame 51 descends under the drive of the drive unit 52, the limiting block 523 can block and limit the lifting frame 51, preventing the lifting frame 51 from descending excessively and disengaging from the lead screw 522. When replacing the hydrogen cylinder body 3 after the UAV lands, the drive unit 52 drives the lifting frame 51 to descend. When the lower part of the lifting frame 51 contacts the limiting block 523, the lifting frame 51 stops descending. At this time, the rotating part 41 slides completely back into the rotating groove 21, ensuring that the support sleeve 4 can rotate freely to disassemble the hydrogen cylinder body 3, while preventing the lifting frame 51 from continuing to descend, which could cause the support sleeve 4 to fall, the hydrogen cylinder body 3 to be damaged, or the pipeline to break. The limit block 523 has a simple structural design and can achieve mechanical limit of the lifting frame 51 without additional control components, which improves the safety and reliability of the lifting unit 5, avoids equipment damage and safety hazards caused by excessive descent of the lifting frame 51, and can also protect the threaded structure of the lead screw 522 and the lifting frame 51, and extend the service life of the device.

[0045] Reference Figure 6 and Figure 9The bottom of the drone fuselage 1 is vertically provided with multiple limiting rods 11 that slide in cooperation with the lifting frame 51. The multiple limiting rods 11 form a limiting area, and the lifting frame 51 moves up and down within the limiting area.

[0046] Multiple limiting rods 11 are vertically installed at the bottom of the UAV fuselage 1, forming a limiting area. The lifting frame 51 slides with the limiting rods 11 and rises and falls within the limiting area. The limiting rods 11 restrict the horizontal displacement of the lifting frame 51, preventing it from shifting left or right or tilting during lifting and falling, ensuring that the lifting frame 51 always moves smoothly in the vertical direction, thereby driving all support sleeves 4 to rise and fall synchronously and smoothly. At the same time, the setting of the limiting rods 11 can improve the structural stability of the lifting frame 51, preventing the lifting frame 51 from shaking due to vibration or maneuvering during UAV flight, preventing the failure of the cooperation between the support sleeves 4 and rotating parts 41, sliding grooves 22, etc., and ensuring the limiting stability of the hydrogen cylinder body 3. In addition, the sliding cooperation between the limiting rods 11 and the lifting frame 51 is smooth and will not affect the lifting speed of the lifting frame 51, and can also guide the lifting frame 51 to ensure accurate alignment during lifting and falling, further optimizing the working performance of the lifting unit 5 and improving the overall stability and safety of the device.

[0047] Reference Figure 8 and Figure 10 A detection block 53 is fixedly installed on the lead screw 522, and a Hall sensor 54 is installed on one side of the detection block 53.

[0048] A detection block 53 is fixedly installed on the lead screw 522, and a Hall sensor 54 is installed on one side of the detection block 53. When the lifting frame 51 rises to the highest position and the hydrogen cylinder body 3 completes the limit, the detection block 53 is exactly at the front end of the detection end of the Hall sensor 54. The Hall sensor 54 can detect the detection block 53 and confirm that the hydrogen cylinder body 3 has been stably limited. When the UAV experiences vibration or other situations during flight maneuvers, causing relative rotation between the lead screw 522 and the lifting frame 51, the detection block 53 will shift along with the lead screw 522. At this time, the Hall sensor 54 cannot detect the shifted detection block 53, thereby triggering the UAV's safety protection mechanism, causing the UAV to stop high-speed maneuvers and return to its original route, avoiding safety accidents such as hydrogen cylinder falling, pipeline entanglement, or UAV flight instability caused by the loosening of the limit of the hydrogen cylinder body 3. This structure features a redundant design, eliminating the need for manual monitoring by the user. It enables real-time detection of the three limit states of the hydrogen cylinder, promptly identifying any limit anomalies and taking protective measures, significantly improving the flight safety of the drone. At the same time, its simple structure and accurate detection do not affect the normal operation and disassembly efficiency of the device, further enhancing the device's safety protection system.

[0049] Reference Figures 1 to 10The support sleeve 4 is provided with a flame-retardant flocking layer.

[0050] The flame-retardant flocked layer has both flame-retardant and cushioning functions, ensuring that the hydrogen cylinder body 3 located in the support sleeve 4 will not directly collide with the inner wall of the support sleeve 4 when the UAV is maneuvering, thus ensuring flight safety.

[0051] Working principle: In daily use, the hydrogen cylinder body 3 needs to be inserted into the corresponding support sleeve 4 from the top. During insertion, due to the obstruction of the drone body 1 and the relatively long length of the hydrogen cylinder body 3, the support sleeve 4 needs to be manually rotated to allow the hydrogen cylinder body 3 to be smoothly inserted. Additionally, during insertion, the connector 31 on the hydrogen cylinder body 3 needs to be aligned with the locking slot 42 on the support sleeve 4. When the hydrogen cylinder body 3 is fully inserted into the support sleeve 4, the connector 31 of the hydrogen cylinder body 3 is precisely engaged with the locking slot 42, preventing the hydrogen cylinder body 3 from rotating within the support sleeve 4 after insertion. When the support sleeve 4 rotates, the rotating part 41 is positioned in the rotating groove 21, ensuring smooth rotation of the support sleeve 4. Then, the end of the gas supply pipe 6 furthest from the drone body 1 is connected to the connector 31 on the hydrogen cylinder body 3. After all the gas supply pipes 6 are connected to the corresponding connector 31 on the hydrogen cylinder body 3, the lifting unit 5 is activated. Although the connection between the rotating part 41 and the support sleeve 4 is in the upper part of the support sleeve 4, after the hydrogen cylinder body 3 is inserted into the support sleeve 4, the support sleeve 4 with the hydrogen cylinder body 3 can tend to be vertical under its own center of gravity.

[0052] Once all support sleeves 4 have returned to their vertical positions, the lifting unit 5 is activated. The rotary driver 521 drives the lifting frame 51 to rise via the lead screw 522. At this time, the bottom of the lifting frame 51 is far from the limit block 523. When the lifting frame 51 in the lifting unit 5 rises, the rotating component 41 slides from the rotating groove 21 into the sliding groove 22. The rotating component 41, once in the sliding groove 22, cannot rotate within it. Instead, it can only slide along the extension direction of the sliding groove 22 because the diameter of the rotating groove 21 is greater than the width of the sliding groove 22. When the lifting frame 51 rises to its highest position, the upper end of the hydrogen cylinder body 3 abuts against the upper part of the support leg 2, thus completing the limiting of the hydrogen cylinder body 3. Since the lifting process of the lifting frame 51 is jointly realized by the lead screw 522 and the rotary driver 521, vibrations may occur during the maneuver of the UAV, causing relative rotation between the lead screw 522 and the lifting frame 51. That is, the upper limit of the hydrogen cylinder body 3 may loosen due to the above situation. Although it is a low probability event, in order to ensure the flight safety of the UAV, it is still necessary to add a redundant design. That is, a detection block 53 is set on the lead screw 522, and a Hall sensor 54 is set on one side of the lead screw 522 to detect the detection block 53. When the lifting frame 51 rises to its highest position, the detection block 53 is at the front end of the detection end of the Hall sensor 54, and the Hall sensor 54 can detect the detection block 53. If the drone rotates relative to the lead screw 522 and the lifting frame 51 during maneuvering, causing the detection block 53 to shift with the lead screw 522, the Hall sensor 54 will be unable to detect the shifted detection block 53. At this time, the drone will stop high-speed maneuvering and return to its original location.

[0053] When the drone returns to base due to insufficient fuel during normal operation, after the drone lands, the drive unit 52 drives the lifting frame 51 to descend, which in turn drives all the support sleeves 4 to descend synchronously. The limit block 523 set at the bottom of the lead screw 522 limits the descent of the lifting frame 51. When the lower part of the lifting frame 51 contacts the limit block 523, the lifting frame 51 descends to the lowest point. At this time, the rotating part 41 is completely in the rotating groove 21, and the rotary drive 521 stops running. After the user removes the gas supply pipes 6 from the corresponding hydrogen cylinder bodies 3 one by one, rotates and tilts the corresponding support sleeve 4, and then pulls out the hydrogen cylinder body 3 and replaces it with a new hydrogen cylinder body 3. After the replacement is completed, the tilted support sleeve 4 is released, and the support sleeve 4 automatically returns to the vertical state.

[0054] The above embodiments only illustrate one or more implementations of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of protection of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A drone with a quick-change support for a hydrogen storage cylinder, comprising a drone body (1) and legs (2), wherein the legs (2) have multiple vertical structures, and a hydrogen cylinder body (3) is provided on one side of each of the multiple vertical structures. Its features are, The vertical structure is provided with a rotating groove (21), which is circular. A sliding groove (22) is vertically provided on the upper part of the rotating groove (21). The sliding groove (22) is connected to the rotating groove (21). The diameter of the rotating groove (21) is greater than the width of the sliding groove (22). The drone also includes: Multiple support sleeves (4) are provided, each corresponding to one of the number of vertical structures. The support sleeves (4) are rotatably provided on one side of the vertical structure. The rotating component (41) is connected to the support sleeve (4) and extends into the rotating groove (21). The outer periphery of the rotating component (41) has two curved surfaces that can simultaneously slide with the inner wall of the rotating groove (21). The centers of the two curved surfaces coincide and the maximum distance between the two curved surfaces is the same as the diameter of the rotating groove (21). The outer periphery of the rotating component (41) also includes two parallel planes. The two curved surfaces are connected by the two planes, and the straight distance between the two planes is the same as the width of the sliding groove (22). The lifting unit (5) is located at the bottom of the UAV body (1) and is used to simultaneously drive all the support sleeves (4) to lift.

2. The UAV with a quick-change bracket for hydrogen storage cylinders according to claim 1, characterized in that, The connection between the rotating component (41) and the support sleeve (4) is located in the upper half of the support sleeve (4).

3. The drone with a quick-change bracket for hydrogen storage cylinders according to claim 1, characterized in that, The side of the hydrogen cylinder body (3) is provided with a connector (31), and the upper part of the support sleeve (4) is provided with a bayonet (42), which engages with the connector (31).

4. The UAV with a quick-change bracket for hydrogen storage cylinders according to claim 1, characterized in that, The lifting unit (5) includes: The lifting frame (51) is vertically movable and disposed at the lower part of the UAV fuselage (1), and the lifting frame (51) is hinged to the support sleeve (4); A drive unit (52) is disposed between the lifting frame (51) and the UAV body (1) for driving the lifting frame (51) to move.

5. A drone with a quick-change bracket for a hydrogen storage cylinder according to claim 4, characterized in that, The drive unit (52) includes: A rotary drive (521) is disposed at the lower part of the fuselage (1) of the UAV; A lead screw (522) is vertically fixed on the output end of the rotary driver (521). The lead screw (522) passes through the lifting frame (51) and is threadedly engaged with the lifting frame (51).

6. A drone with a quick-change bracket for a hydrogen storage cylinder according to claim 5, characterized in that, A limiting block (523) is fixedly provided at the bottom of the lead screw (522), and the maximum length of the limiting block (523) on the horizontal plane is greater than the diameter of the lead screw (522).

7. A drone with a quick-change bracket for a hydrogen storage cylinder according to claim 4, characterized in that, The bottom of the drone fuselage (1) is vertically provided with multiple limiting rods (11) that slide in cooperation with the lifting frame (51). The multiple limiting rods (11) form a limiting area, and the lifting frame (51) rises and falls within the limiting area.

8. A drone with a quick-change bracket for a hydrogen storage cylinder according to claim 5, characterized in that, A detection block (53) is fixedly installed on the lead screw (522), and a Hall sensor (54) is installed on one side of the detection block (53).

9. A drone with a quick-change bracket for a hydrogen storage cylinder according to claim 1, characterized in that, The support sleeve (4) is provided with a flame-retardant flocking layer.

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