A self-adjusting landing structure for unmanned aerial vehicles

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) technology and discloses a self-adjusting landing structure for UAVs. The structure includes a UAV body, a mounting base fixedly mounted on the UAV body, a mounting plate at the bottom of the mounting base, grooves and slots on the outer wall of the mounting plate, a locking disc on the outer wall of the mounting plate, and a locking rod on the outer wall of the mounting plate. Through the linkage design of the buffer airbag and the air outlet component, adaptive adjustment to different ground hardness is achieved. When the UAV lands, the internal air pressure of the buffer airbag increases after being compressed, and the pressure pushes the sealing plate to slide open the air hole for pressure relief. The greater the impact force, the larger the air hole opening, the faster the pressure relief speed, and the stronger the buffering effect. Whether it is the high impact of hard cement ground or the continuous compression of soft sand, this structure can dynamically adjust the buffering force to avoid excessive vibration or sinking of the fuselage, effectively protecting the precision equipment inside the UAV and significantly improving landing safety.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a self-adjusting landing structure for UAVs. Background Technology

[0002] With the widespread application of drones in fields such as aerial surveying, logistics transportation, and emergency rescue, the safety and stability of their landing process have become key factors restricting technological development. In actual operations, drones often need to land in complex and ever-changing environments, such as mountains, water surfaces, and uneven ground, posing many challenges to traditional landing structures.

[0003] Existing drone landing devices typically employ a fixed-rigidity buffer structure. When a drone lands on hard ground, this fixed-rigidity buffer structure cannot absorb large impact forces in time, which can easily lead to severe vibrations of the fuselage or even damage to internal precision equipment. On soft ground, excessive buffering may cause the fuselage to tilt or sink, thereby reducing the landing safety and reliability of the drone in complex environments. Therefore, we have introduced a self-adjusting landing structure for drones. Utility Model Content

[0004] To address the shortcomings of existing technologies, this invention provides a self-adjusting landing structure for unmanned aerial vehicles (UAVs), which has the advantages of adaptive adjustment and a support frame that is easy to install and disassemble, thus solving the problems mentioned in the background art.

[0005] This utility model provides the following technical solution: a self-adjusting landing structure for a drone, comprising a drone body, a mounting base fixedly mounted on the drone body, a mounting plate at the bottom of the mounting base, a sliding groove and a slot respectively formed on the outer wall of the mounting plate, a locking disc and a locking rod on the outer wall of the mounting plate, a fixing post fixedly mounted on the locking rod, an arc-shaped groove formed on the outer wall of the locking disc, a connecting plate fixedly mounted on the mounting plate, a buffer airbag formed on the outer wall of the connecting plate, an air outlet assembly formed on the outer wall of the buffer airbag, the air outlet assembly comprising a tube, a limiting base plate fixedly mounted on the inner wall of the tube, a sealing plate and a first spring respectively formed in the inner cavity of the tube, an air hole formed on the outer wall of the tube, a tube fixedly sleeved on the inner wall of the buffer airbag, a lock assembly formed on the inner wall of the mounting plate, an inflation assembly formed at the bottom of the mounting plate, and a pin fixedly mounted on the locking disc.

[0006] As a preferred technical solution of this utility model: the lock assembly includes a cylindrical body, the inner cavity of the cylindrical body is provided with a lock ball and a second spring, the outer wall of the pin is provided with a ball groove, and the cylindrical body is fixedly installed on the inner wall of the mounting plate.

[0007] As a preferred technical solution of this utility model: the diameter of the lock ball is larger than the opening diameter of the cylinder, the second spring is located on one side of the lock ball, one end of which overlaps with the outer wall of the lock ball, and the other end of which overlaps with the inner wall of the cylinder, and the outer wall of the lock ball is adapted to the shape of the inner wall of the ball groove.

[0008] As a preferred technical solution of this utility model: the inflation assembly includes a corrugated telescopic tube, the outer wall of the corrugated telescopic tube is provided with a throttle valve, the inner wall of the corrugated telescopic tube is fixedly installed with a piston plate, the outer wall of the piston plate is inlaid with a counterweight ball, the outer wall of the corrugated telescopic tube is provided with an air pipe, the inner cavity of the air pipe is respectively fixedly installed with an arc-shaped ring and an annular base, and the inner cavity of the air pipe is respectively provided with a sphere and a third spring.

[0009] As a preferred technical solution of this utility model: the inflation assembly is regarded as a set of movable components, and there are four sets of movable components, which are arranged in a circular array. The tops of the four corrugated telescopic tubes are fixedly connected to the bottom of the locking disc. One end of the four air pipes is connected to the air outlet of the corrugated telescopic tube, and the other end is connected to the air inlet of the buffer airbag. The four spheres and the third spring are located in the middle of the arc ring and the annular base. The diameter of the four spheres is larger than the opening diameter of the arc ring. The four third springs are located on one side of the spheres, with one end overlapping the outer wall of the sphere and the other end overlapping the annular base. The four throttle valves are connected to the air inlet of the corrugated telescopic tube.

[0010] As a preferred technical solution of this utility model: the sliding groove, locking rod, fixing column, and arc groove are regarded as a set of movable components, and there are four sets of movable components, which are arranged in a circular array. The outer walls of the four locking rods are slidably fitted to the inner walls of the sliding grooves, the inner walls of the four arc grooves are slidably fitted to the outer walls of the fixing columns, the outer walls of the four locking rods are adapted to the shape of the outer wall of the mounting base, the outer wall shape of the pin is adapted to the shape of the inner wall of the slot, the outer wall of the sealing plate is slidably fitted to the inner wall of the tube, and the first spring is located on one side of the sealing plate, with one end overlapping the outer wall of the sealing plate and the other end overlapping the inner wall of the limiting base plate.

[0011] Compared with the prior art, the present invention has the following beneficial effects:

[0012] 1. The drone's self-adjusting landing structure, through the linkage design of the buffer airbag and the air outlet component, achieves adaptive adjustment to different ground hardness. When the drone lands, the internal air pressure of the buffer airbag increases after being compressed. The pressure pushes the sealing plate to slide open the air hole to release pressure. The greater the impact force, the larger the air hole opening, the faster the pressure release speed, and the stronger the buffering effect. Whether it is the high impact of hard cement ground or the continuous compression of soft sand, this structure can dynamically adjust the buffering force to avoid excessive vibration or sinking of the fuselage, effectively protect the drone's internal precision equipment, and significantly improve landing safety.

[0013] 2. The drone's self-adjusting landing structure, through the linkage design of four sets of circularly arrayed inflatable components and locking rods, enables the counterweight ball to trigger the synchronous compression of the four sets of corrugated telescopic tubes at the moment of landing, quickly inflating the cushioning airbag and ensuring timely expansion of the cushioning airbag to provide support. At the same time, the rotating locking disc drives the four sets of locking rods to simultaneously tighten and snap onto the mounting base, forming a stable support frame. If it is necessary to replace or upgrade parts, the four locking rods can be snapped off from the mounting base by rotating the locking disc in the opposite direction, effectively improving the versatility and maintainability of the structure. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0015] Figure 2 This is a schematic cross-sectional view of the present invention.

[0016] Figure 3 This is a schematic diagram of the mounting base structure of this utility model;

[0017] Figure 4 This is a schematic diagram of the mounting clip structure of this utility model;

[0018] Figure 5 This is a schematic diagram of the inflatable component structure of this utility model;

[0019] Figure 6 This utility model Figure 2 Enlarged structural diagram at point A in the middle;

[0020] Figure 7 This utility model Figure 2 Enlarged structural diagram at point B;

[0021] Figure 8 This utility model Figure 5 Enlarged structural diagram at point C.

[0022] In the diagram: 1. Unmanned aerial vehicle (UAV) body; 2. Mounting base; 3. Mounting plate; 4. Slide groove; 5. Slot; 6. Locking disc; 7. Locking rod; 8. Fixing column; 9. Arc groove; 10. Connecting plate; 11. Buffer airbag; 12. Air outlet assembly; 13. Lock assembly; 14. Inflation assembly; 15. Pin; 121. Tube body; 122. Sealing plate; 123. First spring; 124. Limiting base plate; 125. Air hole; 131. Cylinder body; 132. Lock ball; 133. Second spring; 134. Ball groove; 141. Corrugated telescopic tube; 142. Throttle valve; 143. Piston plate; 144. Counterweight ball; 145. Air pipe; 146. Sphere; 147. Arc ring; 148. Third spring; 149. Annular base. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Please see Figure 1 - Figure 8 A self-adjusting landing structure for a drone includes a drone body 1, a mounting base 2 fixedly mounted on the drone body 1, a mounting plate 3 at the bottom of the mounting base 2, a sliding groove 4 and a slot 5 respectively formed on the outer wall of the mounting plate 3, a locking disc 6 formed on the outer wall of the mounting plate 3, a locking rod 7 formed on the outer wall of the mounting plate 3, a fixing post 8 fixedly mounted on the locking rod 7, an arc-shaped groove 9 formed on the outer wall of the locking disc 6, a connecting plate 10 fixedly mounted on the mounting plate 3, and a buffer airbag 11 formed on the outer wall of the connecting plate 10. The outer wall of the buffer airbag 11 is provided with an air outlet assembly 12, which includes a tube body 121. A limit base plate 124 is fixedly installed on the inner wall of the tube body 121. A sealing plate 122 and a first spring 123 are respectively provided in the inner cavity of the tube body 121. An air hole 125 is opened on the outer wall of the tube body 121. The inner wall of the buffer airbag 11 is fixedly sleeved with the tube body 121. The inner wall of the mounting plate 3 is provided with a lock assembly 13. An inflation assembly 14 is provided at the bottom of the mounting plate 3. A pin 15 is fixedly installed on the locking plate 6.

[0025] In the above structure, by setting the buffer airbag 11 and the air outlet assembly 12, after the mounting plate 3 and the locking plate 6 are snapped together by the lock assembly 13, the mounting plate 3 and the locking plate 6 are placed at the bottom of the mounting base 2. Then, by rotating the locking plate 6, the locking rod 7 and the fixing post 8 slide relative to each other using the rotating locking plate 6. This causes the locking rod 7 to snap onto the outer wall of the mounting base 2. When the buffer airbag 11 is installed at the bottom of the locking plate 6 using the connecting plate 10, the buffer airbag 11 will inflate using the transmission mechanism of the parts in the inflation assembly 14 during flight and landing of the unmanned aerial vehicle 1. The airbag 11 will deform in volume under the inflation of the gas, thus... When the deformable airbag 11 comes into contact with the ground, the airbag 11 uses the gas in its inner cavity to cooperate with the air outlet component 12. Under the relative compression between the ground and the UAV body 1, the gas in the inner cavity of the airbag 11 is pressurized, causing the sealing plate 122 to slide along the inner wall of the tube 121 under the push of the increased gas pressure. This causes the first spring 123 to be compressed, and the sealing plate 122 opens the air hole 125 when it slides. This allows the gas in the inner cavity of the airbag 11 to be discharged through the air hole 125. The depressurization rate of the airbag 11 automatically changes with the impact force of the UAV body 1, so that the UAV body 1 can adapt to different ground hardness for landing.

[0026] In a preferred embodiment: the lock assembly 13 includes a cylinder 131, the inner cavity of the cylinder 131 is provided with a lock ball 132 and a second spring 133, the outer wall of the pin 15 is provided with a ball groove 134, and the inner wall of the mounting plate 3 is fixedly installed with the cylinder 131.

[0027] In a preferred embodiment: the diameter of the lock ball 132 is larger than the opening diameter of the cylinder 131, the second spring 133 is located on one side of the lock ball 132, one end of which overlaps with the outer wall of the lock ball 132, and the other end overlaps with the inner wall of the cylinder 131. The outer wall of the lock ball 132 is adapted to the shape of the inner wall of the ball groove 134.

[0028] In the above structure, by setting the lock ball 132 and the second spring 133, the locking disc 6 is first inserted into the inner cavity of the slot 5 through the pin 15. The pin 15 inserted into the inner cavity of the slot 5 will squeeze the lock ball 132, which will then drive the second spring 133 to compress. The lock ball 132 will then retract into the inner cavity of the cylinder 131. When the locking disc 6 is rotated, the pin 15 will rotate with the rotation of the locking disc 6. The rotating pin 15 will then drive the ball groove 134 to rotate. When the ball groove 134 rotates to be opposite the lock ball 132, the lock ball 132 will be reset by the rebound of the second spring 133 and inserted into the inner cavity of the ball groove 134. This will fix the lock ball 132 to the opening of the cylinder 131, thereby completing the installation connection between the locking disc 6 and the mounting plate 3.

[0029] In a preferred embodiment: the inflation assembly 14 includes a corrugated telescopic tube 141, the outer wall of the corrugated telescopic tube 141 is provided with a throttle valve 142, the inner wall of the corrugated telescopic tube 141 is fixedly installed with a piston plate 143, the outer wall of the piston plate 143 is inlaid with a counterweight ball 144, the outer wall of the corrugated telescopic tube 141 is provided with an air pipe 145, the inner cavity of the air pipe 145 is fixedly installed with an arc-shaped ring 147 and an annular base 149, and the inner cavity of the air pipe 145 is provided with a ball 146 and a third spring 148.

[0030] In a preferred embodiment: the inflation assembly 14 is considered as a set of movable assemblies, and there are four sets of movable assemblies arranged in a circular array. The tops of the four corrugated telescopic tubes 141 are fixedly connected to the bottom of the locking disc 6. One end of the four air pipes 145 is connected to the air outlet of the corrugated telescopic tubes 141, and the other end is connected to the air inlet of the buffer airbag 11. The four spheres 146 and the third springs 148 are located in the middle of the arc ring 147 and the annular base 149. The diameter of the four spheres 146 is larger than the opening diameter of the arc ring 147. The four third springs 148 are located on one side of the spheres 146, with one end overlapping the outer wall of the spheres 146 and the other end overlapping the annular base 149. The four throttle valves 142 are connected to the air inlet of the corrugated telescopic tubes 141.

[0031] In the above structure, by setting the corrugated telescopic tube 141, the counterweight ball 144 of the UAV body 1 contacts the ground first when it lands. This causes the corrugated telescopic tube 141 to compress during landing, compressing the gas inside the tube through the piston plate 143. When the compressed air is transmitted into the buffer airbag 11 via the air pipe 145, the sphere 146 inside the air pipe 145 is pushed by the gas, causing the third spring 148 to compress. This opens the arc-shaped ring 147, allowing the gas to... The air is transmitted into the inner cavity of the airbag 11 through the air tube 145. At the same time, when the UAV body 1 is taking off, its corrugated telescopic tube 141 extends due to the weight of the counterweight ball 144. When the corrugated telescopic tube 141 extends, the throttle valve 142 opens to draw in the outer cavity of the corrugated telescopic tube 141. After the corrugated telescopic tube 141 is reset, the throttle valve 142 closes, thus preparing for the next air intake of the airbag 11. At the same time, the four sets of inflation components 14 can inflate the airbag 11 through the same operation, so that the airbag 11 is more stable during inflation.

[0032] In a preferred embodiment: the slide 4, locking rod 7, fixing post 8, and arc groove 9 are regarded as a set of movable components, and there are four sets of movable components, which are arranged in a circular array. The outer walls of the four locking rods 7 are slidably fitted to the inner walls of the slide 4, the inner walls of the four arc grooves 9 are slidably fitted to the outer walls of the fixing posts 8, the outer walls of the four locking rods 7 are adapted to the shape of the outer wall of the mounting base 2, the outer wall shape of the pin 15 is adapted to the shape of the inner wall of the slot 5, the outer wall of the sealing plate 122 is slidably fitted to the inner wall of the tube 121, and the first spring 123 is located on one side of the sealing plate 122, with one end overlapping the outer wall of the sealing plate 122 and the other end overlapping the inner wall of the limiting base plate 124.

[0033] In the above structure, by setting the sliding groove 4, locking rod 7, fixing post 8, and arc-shaped groove 9, rotating the locking disc 6 causes the four arc-shaped grooves 9 to rotate accordingly. This rotation of the four arc-shaped grooves 9 then drives the four fixing posts 8 to move synchronously. The moving fixing posts 8 then drive the four locking rods 7 to slide relative to each other along the inner walls of the four sliding grooves 4. This causes the outer walls of the four locking rods 7 to engage with the outer wall of the mounting base 2. Furthermore, rotating the locking disc 6 causes the four locking rods 7 to tighten and engage with the outer wall of the mounting base 2. The buffer airbag 11 is mounted at the bottom of the locking disc 6 via the connecting plate 10, thus securing the buffer airbag... 11 When the UAV body 1 is subjected to landing force, the gas in the inner cavity of its buffer airbag 11 is pushed by the pressure to slide the sealing plate 122 along the inner wall of the tube body 121. The sliding sealing plate 122 will drive the first spring 123 to be compressed. When the sealing plate 122 slides to the position of the air hole 125, the gas will be discharged through the air hole 125. The gas inside the buffer airbag 11 is depressurized through the air hole 125, so that the gas depressurization rate changes automatically with the impact force on the buffer airbag 11. When the impact force is large, the air pressure rises rapidly and the depressurization is faster, which increases the buffering effect and adapts to landing on different ground hardnesses.

[0034] Working principle: First, insert the pin 15 into the slot 5 of the mounting plate 3, causing the pin 15 to press against the lock ball 132, compress the second spring 133, and retract into the inner cavity of the cylinder 131. Then, rotate the locking disc 6, causing the pin 15 to rotate. When the ball groove 134 rotates to align with the lock ball 132, the second spring 133 rebounds, pushing the lock ball 132 into the ball groove 134, thus completing the initial fixation between the locking disc 6 and the mounting plate 3. Then, the mounting plate 3 and the locking disc 6 are combined. The body is placed at the bottom of the mounting base 2, and then the locking plate 6 is rotated, which causes the four rotating arc grooves 9 to drive the four fixed columns 8 to move synchronously. The four fixed columns 8 will then drive the four locking rods 7 to slide relative to each other along the inner wall of the four sliding grooves 4, so that the outer wall of the four locking rods 7 will be engaged with the outer wall of the mounting base 2. At the same time, the top of the four sets of inflatable components 14 is fixed to the bottom of the locking plate 6, and then the air pipe 145 is connected to the air inlet of the buffer airbag 11 to complete the overall installation.

[0035] Secondly, when the UAV takes off, its counterweight ball 144 causes the corrugated telescopic tube 141 to extend due to its own weight. As the tube extends, the throttle valve 142 opens, allowing outside air to be drawn into the inner cavity of the tube. After the tube returns to its original position, the throttle valve 142 closes, and the four inflation components 14 simultaneously pre-store gas, preparing for the inflation of the cushioning airbag 11 during landing. Then, when the UAV lands, the counterweight ball 144 first contacts the ground, causing it to compress the corrugated telescopic tube 141. This compression, in turn, causes the piston plate 143 to squeeze the air inside the tube, pushing the sphere 146 and compressing the third spring 148. This opens the arc-shaped ring 147, allowing gas to quickly inflate the cushioning airbag 11 through the air pipe 145. The four inflation components 14 work simultaneously to ensure the rapid inflation of the cushioning airbag 11. The expansion causes the airbag 11 to expand, and upon contact with the ground, it is compressed by the impact force of the drone body 1. The internal air pressure increases, and the pressure pushes the sealing plate 122 to slide along the inner wall of the tube 121 and compress the first spring 123. When the sealing plate 122 slides to the position of the air hole 125, the air hole 125 opens, and the gas is discharged. The greater the impact force, the faster the air pressure rises, the greater the sliding distance of the sealing plate 122, the larger the opening of the air hole 125, and the faster the gas depressurization speed. In this way, the cushioning force can be automatically adjusted according to the hardness of the ground. At the same time, when the drone body 1 takes off again, the counterweight ball 144 rises with the drone body 1, driving the corrugated telescopic tube 141 to extend and suck in air to reset, causing the throttle valve 142 to close. This allows the sealing plate 122 to reset and close the air hole 125 under the action of the first spring 123 without the push of gas, returning it to its initial state and waiting for the next landing adjustment.

[0036] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A self-adjusting landing structure for an unmanned aerial vehicle (UAV), comprising an UAV body (1), characterized in that: The unmanned aerial vehicle (1) is fixedly mounted with a mounting base (2). A mounting plate (3) is provided at the bottom of the mounting base (2). The outer wall of the mounting plate (3) is provided with a sliding groove (4) and a slot (5). A locking disc (6) is provided on the outer wall of the mounting plate (3). A locking rod (7) is provided on the outer wall of the mounting plate (3). A fixing post (8) is fixedly mounted on the locking rod (7). An arc-shaped groove (9) is provided on the outer wall of the locking disc (6). A connecting plate (10) is fixedly mounted on the mounting plate (3). A buffer airbag (11) is provided on the outer wall of the connecting plate (10). The buffer airbag (11)... An air outlet assembly (12) is provided on the outer wall. The air outlet assembly (12) includes a tube body (121). A limiting base plate (124) is fixedly installed on the inner wall of the tube body (121). A sealing plate (122) and a first spring (123) are respectively provided in the inner cavity of the tube body (121). An air hole (125) is opened on the outer wall of the tube body (121). The inner wall of the buffer airbag (11) is fixedly sleeved with the tube body (121). A lock assembly (13) is provided on the inner wall of the mounting plate (3). An inflation assembly (14) is provided at the bottom of the mounting plate (3). A pin (15) is fixedly assembled on the locking disc (6).

2. The self-adjusting landing structure for a UAV according to claim 1, characterized in that: The lock assembly (13) includes a cylinder (131), the inner cavity of the cylinder (131) is provided with a lock ball (132) and a second spring (133), the outer wall of the pin (15) is provided with a ball groove (134), and the inner wall of the mounting plate (3) is fixedly installed with the cylinder (131).

3. The self-adjusting landing structure for a UAV according to claim 2, characterized in that: The diameter of the lock ball (132) is larger than the opening diameter of the cylinder (131). The second spring (133) is located on one side of the lock ball (132), with one end overlapping the outer wall of the lock ball (132) and the other end overlapping the inner wall of the cylinder (131). The outer wall of the lock ball (132) is adapted to the shape of the inner wall of the ball groove (134).

4. The self-adjusting landing structure for a UAV according to claim 1, characterized in that: The inflation assembly (14) includes a corrugated telescopic tube (141), the outer wall of which is provided with a throttle valve (142), the inner wall of which is fixedly installed with a piston plate (143), the outer wall of which is inlaid with a counterweight ball (144), the outer wall of which is provided with an air pipe (145), the inner cavity of which is fixedly installed with an arc ring (147) and an annular base (149), and the inner cavity of which is provided with a sphere (146) and a third spring (148).

5. The self-adjusting landing structure for a UAV according to claim 4, characterized in that: The inflation assembly (14) is considered as a set of movable components, and there are four sets of movable components arranged in a circular array. The top of the four corrugated telescopic tubes (141) is fixedly connected to the bottom of the locking disc (6). One end of the four air pipes (145) is connected to the air outlet of the corrugated telescopic tube (141), and the other end is connected to the air inlet of the buffer airbag (11). The four spheres (146) and the third spring (148) are located in the middle of the arc ring (147) and the annular base (149). The diameter of the four spheres (146) is larger than the opening diameter of the arc ring (147). The four third springs (148) are located on one side of the spheres (146), and one end overlaps with the outer wall of the spheres (146), and the other end overlaps with the annular base (149). The four throttle valves (142) are connected to the air inlet of the corrugated telescopic tubes (141).

6. The self-adjusting landing structure for a UAV according to claim 1, characterized in that: The slide groove (4), locking rod (7), fixing column (8), and arc groove (9) are considered as a set of movable components, and there are four sets of movable components, which are arranged in a circular array. The outer walls of the four locking rods (7) are fitted and slidably disposed with the inner wall of the slide groove (4). The inner walls of the four arc grooves (9) are fitted and slidably disposed with the outer wall of the fixing column (8). The outer walls of the four locking rods (7) are adapted to the shape of the outer wall of the mounting base (2). The outer wall shape of the pin (15) is adapted to the shape of the inner wall of the slot (5). The outer wall of the sealing plate (122) is fitted and slidably disposed with the inner wall of the tube body (121). The first spring (123) is located on one side of the sealing plate (122), and one end overlaps with the outer wall of the sealing plate (122), and the other end overlaps with the inner wall of the limiting base plate (124).

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