Unmanned aerial vehicle landing buffer frame

Abstract

The application relates to an unmanned aerial vehicle landing buffer frame, which comprises an unmanned aerial vehicle body, a rotor and a gas cylinder, the bottom of the unmanned aerial vehicle body is provided with a plurality of foot support sleeves, a fixed mounting sleeve is arranged in the foot support sleeve, an adjusting inner sleeve is arranged in the fixed mounting sleeve, a foot support is arranged in the adjusting inner sleeve in a sliding mode, a foot support plug and a tower top plug are arranged in the fixed mounting sleeve, a first sliding hole is formed in the foot support plug, a striker is arranged in the first sliding hole in a sliding mode, and a foot support spring is connected between the striker and the foot support plug. In the structure, the spring is added in the installation process of the foot support, so that the unmanned aerial vehicle can be subjected to a certain buffering force when landing, and the mounted articles can be prevented from being damaged due to collision; meanwhile, the pressure of the unmanned aerial vehicle body on the foot support when landing pushes the foot support spring to compress, the striker on the foot support sleeve moves upward, hits the ejection pad above, the whole gas cylinder clamping structure is loosened, the gas cylinder can be easily taken out from the body, and the labor cost is reduced.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a UAV landing buffer. Background Technology

[0002] A multi-rotor drone is a special type of unmanned rotary-wing aircraft with three or more rotor shafts. It can generate lift and thrust through various power sources. In addition to normal flight functions, it can sometimes carry and transport goods. Therefore, drones generally have relatively high energy consumption and require frequent replacement of batteries and other energy sources during actual use.

[0003] In the field of hydrogen-powered drones, hydrogen cylinders are a component that needs to be replaced frequently to ensure the continuity of the drone's operations. Conventional hydrogen cylinder fixing structures mostly use guide rails, buckles, straps and other fixing methods. After landing, manual contact and fixing are required, and then the hydrogen cylinder is removed, which incurs certain labor costs. Furthermore, when the drone body lands directly, it may cause damage to expensive items and components that are mounted on it.

[0004] Therefore, a drone landing gear with buffer force is designed to not only provide the drone with a buffer force to prevent the attached items from being damaged by collision, but also to automatically release the fixed structure during the buffering process, so as to easily replace the gas cylinder. Summary of the Invention

[0005] The purpose of this invention is to provide a buffer landing gear for unmanned aerial vehicles (UAVs) to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a drone landing buffer frame, comprising a drone fuselage, rotor, and gas cylinder. Multiple landing gear sleeves are provided at the bottom of the drone fuselage. A fixed mounting sleeve is installed inside each landing gear sleeve. An adjusting inner sleeve is installed inside the fixed mounting sleeve. A foot support is slidably mounted inside the adjusting inner sleeve. A landing gear plug and a tower top plug are provided inside the fixed mounting sleeve. A first sliding hole is formed on the landing gear plug, and a striker is slidably mounted inside the first sliding hole. A landing gear spring connects the striker and the landing gear plug. A second sliding hole is formed on the tower top plug, and a clamping rod is slidably mounted inside the second sliding hole. A push-out pad is provided at the bottom of the clamping rod, and a clamping spring connects the push-out pad and the tower top plug.

[0007] Preferably, the adjusting inner sleeve passes through the leg sleeve.

[0008] Preferably, both the adjusting inner sleeve and the tower top plug are provided with O-rings, and the O-rings are in frictional contact with the foot bracket and the clamping rod, respectively.

[0009] Preferably, the adjusting inner sleeve is screwed into the fixed mounting sleeve via a threaded assembly.

[0010] Preferably, both the firing pin and the ejector pad have flange edges extending outwards.

[0011] Preferably, the fixed mounting sleeve has a partition in the middle, and the partition has a through hole.

[0012] Preferably, the tripod end is located below the partition, and the ejector pad is located above the partition.

[0013] Preferably, the fixed mounting sleeve has a guide rail, and a guide block is provided on the left side of the flange edge located on the ejector pad.

[0014] Preferably, a gas cylinder clamping mechanism is provided between the tops of the clamping rods. The gas cylinder clamping mechanism includes bearing seats and straps, and a strap is connected between every two bearing seats.

[0015] Preferably, the tripod end has two air pressure balance holes.

[0016] Compared with the prior art, the beneficial effects of this invention are as follows: In this structure, by installing foot brackets, the drone is supported for take-off, landing, and flat placement, increasing the distance between the drone and the ground during landing, thereby protecting the drone and its many expensive attachments and components. Furthermore, by adding springs during the installation of the foot brackets, the drone receives a certain amount of cushioning force during landing, preventing damage to the attached items from collisions. Simultaneously, the pressure of the drone's fuselage on the foot brackets during landing compresses the foot bracket springs, causing the striker on the foot bracket sleeve to move upward and strike the ejector pad above, thereby loosening the entire gas cylinder clamping structure and allowing the gas cylinder to be easily removed from the fuselage, reducing labor costs. The adjusting inner sleeve and related elastic structures are independently assembled, allowing for disassembly and reassembly to adapt to different volumes required for different working states of the drone. They can also be adjusted vertically within the fixed mounting sleeve, allowing the distance between the striker and the ejector pad to be adjusted. This ensures that the ejector pad will not easily pop out during take-off or landing under different conditions, preventing the fixed components from shaking and affecting flight safety. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the main three-dimensional structure of the present invention;

[0018] Figure 2 This is a partial three-dimensional structural schematic diagram of the present invention;

[0019] Figure 3 This is a top view of part of the structure of the present invention;

[0020] Figure 4This is a three-dimensional schematic diagram of the foot support and gas cylinder clamping structure in this invention;

[0021] Figure 5 This is an exploded view of the adjusted structure in this invention;

[0022] Figure 6 This is a cross-sectional view of the adjusted structure in this invention.

[0023] Labels in the diagram: 1-UAV fuselage, 2-rotor, 3-gas cylinder, 4-footrest sleeve, 5-fixed mounting sleeve, 6-adjusting inner sleeve, 7-foot bracket, 8-footrest plug, 9-tower top plug, 10-first sliding hole, 11-firing pin, 12-footrest spring, 13-second sliding hole, 14-clamping rod, 15-ejection pad, 16-clamping spring, 17-O-ring seal, 18-threaded assembly, 19-flange edge, 20-partition plate, 21-through hole, 22-guide rail, 23-guide block, 24-gas cylinder clamping mechanism, 25-bearing seat, 26-strap, 27-pressure balance hole. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] Example 1

[0026] like Figures 1 to 6The drone landing pad shown includes a drone fuselage 1, rotor 2, foot brackets 7, and gas cylinder 3. Multiple foot bracket sleeves 4 are located at the bottom of the drone fuselage 1. Fixed mounting sleeves 5 are installed inside the foot bracket sleeves 4. Adjustable inner sleeves 6 are installed inside the fixed mounting sleeves 5. Foot brackets 7 are slidably mounted inside the adjustable inner sleeves 6. Foot plugs 8 and tower plugs 9 are located inside the fixed mounting sleeves 5. A first sliding hole 10 is formed on the foot plug 8, and a striker 11 is slidably mounted inside the first sliding hole 10. A foot spring 12 connects the striker 11 to the foot plug 8. A second sliding hole 13 is formed on the tower plug 9, and a clamping rod 14 is slidably mounted inside the second sliding hole 13. A push-out pad 15 is located at the bottom of the clamping rod 14, and a clamping spring 16 connects the push-out pad 15 to the tower plug 9. The adjustable inner sleeve 6 passes through the foot bracket sleeves 4. Both the inner sleeve 6 and the tower top plug 9 are equipped with O-rings 17, which are in frictional contact with the foot bracket 7 and the clamping rod 14, respectively. The inner sleeve 6 is screwed into the fixed installation sleeve 5 through the threaded assembly 18. The outer sides of the striking pin 11 and the ejector pad 15 are both provided with flange edges 19. The middle of the fixed installation sleeve 5 is provided with a partition 20, and a through hole 21 is opened on the partition 20. The foot plug 8 is located below the partition 20, and the ejector pad 15 is located above the partition 20. The fixed installation sleeve 5 is provided with a guide rail 22, and a guide block 23 is provided on the left side of the flange edge 19 on the ejector pad 15. A gas cylinder clamping mechanism 24 is provided between the tops of the clamping rods 14. The gas cylinder clamping mechanism 24 includes a bearing seat 25 and a strap 26, and a strap 26 is connected between every two bearing seats 25. Two air pressure balance holes 27 are opened on the foot plug 8.

[0027] In this structure, the foot bracket 7 serves as a support component for the drone's take-off, landing, and flattening, increasing the distance between the drone and the ground during landing, thus protecting the drone and its many expensive attachments and components. Furthermore, by adding springs during the installation of the foot bracket 7, the drone receives a certain amount of cushioning force during landing, preventing damage to the attached items from collisions. Simultaneously, the pressure of the drone's fuselage on the foot bracket 7 during landing compresses the foot bracket spring 12, causing the striker 11 on the foot bracket sleeve 4 to move upwards and strike the upper ejector block 15, thereby loosening the entire gas cylinder 3 clamping structure and allowing the gas cylinder 3 to be easily removed from the fuselage, reducing labor costs. The adjusting inner sleeve 6 and related elastic structures are independently assembled, allowing for integrated disassembly to adapt to different volumes required for different drone operating states. They can also be adjusted vertically within the fixed mounting sleeve 5, allowing the distance between the striker 11 and the ejector block 15 to be adjusted. This ensures that the ejector block 15 will not easily pop out during take-off or landing under different conditions, preventing the fixed components from shaking and affecting flight safety.

[0028] Example 2

[0029] like Figures 1 to 6The drone landing pad shown includes a drone fuselage 1, rotors 2, foot supports 7, and gas cylinders 3. Multiple rotors 2 are located on the top of the drone fuselage 1. The rotors 2 generate lift by moving air, keeping the drone stable in the air. The number of rotors 2 is usually even, providing power not only during takeoff and landing but also balancing gravity and adjusting position and attitude. Four foot supports 7 are located at the bottom of the drone fuselage 1. The foot supports 7 are the supporting components for takeoff, landing, and flattening of the drone, directly contacting the ground. When the drone is not in flight, the foot supports 7 provide support and fixation. Unlike existing technologies, the gas cylinders 3 of this invention are suspended below the drone fuselage 1. The drone is clamped and fixed below the drone fuselage 1 using a gas cylinder 3 clamping structure. This solves the problem of signal reception and positioning of the positioning module and other modules being obscured by the upper mounting, and also avoids the phenomenon of the gas cylinder 3 being encroached upon by the internal space of the fuselage, resulting in increased overall size and weight, and affecting the drone's flight performance.

[0030] The above embodiment discloses an adjustment structure connected between the gas cylinder 3 clamping structure and the foot bracket 7. When the drone takes off or the fuselage pressure is insufficient, the gas cylinder 3 clamping structure can clamp and fix the gas cylinder 3. When the drone lands, the foot bracket 7 first contacts the ground, and then the drone fuselage 1 generates a downward inertial force, which drives the adjustment structure to operate, causing the gas cylinder 3 clamping structure to loosen and no longer clamp and fix the gas cylinder 3. Then, the gas cylinder 3 can be easily removed, which facilitates the maintenance and replacement of the gas cylinder 3.

[0031] The gas cylinder 3 clamping structure can be any of the following: a limiting strap 26, a limiting guide wheel, a limiting fulcrum, a pin, or a lock, so that the gas cylinder 3 clamping structure can be released when it moves upward. Here, it is limited to a bearing seat 25 and a strap 26. The strap 26 is connected between two bearing seats 25 on the same side. When the strap 26 is taut, it limits the gas cylinder 3 to prevent it from falling, so as to provide power for the drone to fly normally. When the bearing seat 25 moves upward, it will drive the two sides of the strap 26 to move closer together, and then the strap 26 will become loose. Under the influence of gravity, the gas cylinder 3 will automatically fall downward, hook the strap 26 and straighten it downward. At this time, a gap will be created between the gas cylinder 3 and the drone body 1, which is convenient for handling and maintenance.

[0032] Example 3

[0033] like Figures 1 to 6The drone landing pad shown has an adjustment structure connected between the gas cylinder 3 clamping structure and the foot bracket 7. When the drone takes off or the fuselage pressure is insufficient, the gas cylinder 3 clamping structure can clamp and fix the gas cylinder 3. When the drone lands, the foot bracket 7 first contacts the ground, and then the drone fuselage 1 exerts a downward inertial force, which drives the adjustment structure to operate. This causes the gas cylinder 3 clamping structure to loosen and no longer clamp and fix the gas cylinder 3, allowing the gas cylinder 3 to be easily removed, facilitating the maintenance and replacement of the gas cylinder 3.

[0034] Specifically set as follows:

[0035] The drone fuselage 1 has four tripod sleeves 4 at its bottom. The tripod sleeves 4 protrude from the drone fuselage 1 and are fixedly mounted to the inner wall of each sleeve 5 through mounting holes. An adjusting inner sleeve 6 is installed inside the fixed mounting sleeve 5. The adjusting inner sleeve 6 is located in the lower half of the fixed mounting sleeve 5 and extends out of the tripod sleeve 4, so that the tripod 7 can be slidably mounted on the bottom of the adjusting inner sleeve 6. The inner wall of the fixed mounting sleeve is divided into two parts by a partition 20, namely space a and space b from top to bottom. Space b is on the same side as the tripod 7 and has a tripod plug 8 with a first sliding hole. 10. A striking pin 11 is slidably provided in the first sliding hole 10. A foot spring 12 is connected between the striking pin 11 and the foot plug 8. The space a and the gas cylinder 3 clamping structure are on the same side. A tower top plug 9 is provided at the top of the space a. A second sliding hole 13 is opened on the tower top plug 9. A clamping rod 14 is slidably provided in the second sliding hole 13. The clamping rod 14 is used to install the gas cylinder 3 clamping structure (that is, a bearing seat 25 is provided at the top of the clamping rod 14. A strap 26 is connected between the bearing seats 25. The strap 26 fixes the gas cylinder 3). A push-out pad 15 is provided at the bottom of the clamping rod 14. A clamping spring 16 is connected between the push-out pad 15 and the tower top plug 9.

[0036] That is, when the drone lands, after the foot bracket 7 touches the ground, the downward pressure will continue to push the drone body 1 downward, which in turn will cause the adjusting inner sleeve 6 to move downward relative to the foot bracket 7. Then the foot bracket spring 12 is compressed, which will cause the impact pin 11 to move upward. The impact pin 11 moves upward and continues to slide upward through the first sliding hole 10 until it hits the ejector pad 15 and moves upward. At this time, the ejector pad 15 moves upward and causes the clamping rod 14 to move upward in the second sliding hole 13. The clamping structure of the gas cylinder 3 is loosened, that is, the bearing seat 25 moves upward and causes the strap 26 to no longer be tight. Under the influence of gravity, the gas cylinder 3 will automatically fall downward and hook the strap 26 downward and straighten it. At this time, a gap will be created between the gas cylinder 3 and the drone body 1, which will make it easier to take it out for maintenance. In order to enable the firing pin 11 to move upward smoothly, a through hole 21 is provided on the partition plate 20. The firing pin 11 can continue to slide upward smoothly under the guidance of the through hole 21, thereby pushing the ejector pad 15 to move upward and preventing the firing pin 11 from deviating during the movement.

[0037] Example 4

[0038] like Figures 1 to 6 The UAV landing buffer shown has a foot bracket 7 slidably mounted on the bottom of an adjusting inner sleeve 6. An O-ring 17 is provided on the lower outer side of the adjusting inner sleeve 6. Correspondingly, a slightly recessed groove is opened on the top of the foot bracket 7. That is, the adjusting inner sleeve 6 can drive all its internal components to be fixed on the foot bracket 7 through the O-ring 17. The O-ring 17 sinks into the groove and generates frictional contact, effectively realizing the installation of the adjustment structure. Similarly, an O-ring 17 is also provided in the second sliding hole 13 on the tower top plug 9. When the clamping rod 14 moves in the second sliding hole 13, it will make frictional contact with the O-ring 17. When the clamping rod 14 is installed into the tower top plug 9, it can be inserted through the second sliding hole 13 until the groove at the bottom of the clamping rod 14 engages with the O-ring 17, completing the installation.

[0039] Therefore, the fixed mounting sleeve 5 is installed inside the landing gear sleeve 4, while the adjusting inner sleeve 6 is installed inside the fixed mounting sleeve 5. The adjusting inner sleeve 6 is connected to the landing gear 7 via an O-ring seal 17. Operators can then remove the adjusting inner sleeve 6 from the fixed mounting sleeve 5, thereby removing the landing gear plug 8, landing gear spring 12, and impact pin 11 as a single unit, thus dismantling the entire adjustment structure and landing gear 7. The landing gear 7 can also be further disassembled by detaching it from the adjusting inner sleeve 6 via the O-ring seal 17. When the drone is performing a mission, the landing gear 7 can be quickly removed to reduce the overall size and volume, thus reducing the load on the drone fuselage 1, allowing for more flexible and lightweight flight, and extending the drone's operating time.

[0040] Example 5

[0041] Furthermore, the "O-ring 17" provided in Embodiment 4 allows the foot bracket 7 to be easily disassembled when installed at the bottom of the adjusting inner sleeve 6. Without specifying how to disassemble the adjusting inner sleeve 6, this embodiment proposes a threaded assembly 18 connected between the adjusting inner sleeve 6 and the fixed mounting sleeve 5. Specifically, the fixed mounting sleeve 5 has an internal thread on its inner wall, and the adjusting inner sleeve 6 has an external thread on its outer side. After installing the foot bracket 7 on the adjusting inner sleeve 6, the external thread of the adjusting inner sleeve 6 is aligned with the external thread of the fixed mounting sleeve 5. The adjusting inner sleeve 6 is then installed inside the fixed mounting sleeve 5 by turning, indirectly achieving the installation of the foot bracket 7 within the adjusting inner sleeve 6. Simultaneously, the adjusting inner sleeve 6 enters the fixed mounting sleeve 5, causing its internal components to move upwards, and the striking pin 11 aligns with the central through hole 21 on the partition plate 20, preparing for adjustment.

[0042] Furthermore, the inner sleeve 6 and the fixed mounting sleeve 5 are connected by a threaded assembly 18. By adjusting the screw-in depth, the relative position between the impact pin 11 and the ejector pad 15 on the landing gear plug 8 can be changed. When the relative position is increased, more pressure is required to move the ejector pad 15 upward and loosen the gas cylinder 3 clamping structure. Conversely, if the relative position is decreased, the gas cylinder 3 clamping structure can be opened with less pressure. Thus, the relative position between the impact pin 11 and the ejector pad 15 can be adjusted according to the different states or takeoff weights of the UAV, so that the clamping force of the gas cylinder 3 clamping structure is within a certain range, and the loosening and opening is neither too easy nor too difficult.

[0043] Example 6

[0044] Referring to embodiments 3 and 5, the adjustment structure includes: four foot sleeves 4 are provided at the bottom of the UAV fuselage 1, a fixed mounting sleeve 5 is installed inside the foot sleeve 4, and an adjusting inner sleeve 6 is installed inside the fixed mounting sleeve 5 through a threaded assembly 18. The adjusting inner sleeve 6 extends out of the foot sleeve 4, so that the foot support 7 can be slidably installed at the bottom of the adjusting inner sleeve 6; the inner wall of the fixed mounting sleeve is divided into two parts by a partition 20, which are space a and space b from top to bottom. Space b is on the same side as the foot support 7, and a foot plug 8 is provided in space b. A striker 11 is slidably connected to the foot plug 8 through a foot spring 12; a tower top plug 9 is provided in space a, and an ejector pad 15 is slidably provided on the tower top plug 9 through a clamping spring 16.

[0045] In this invention, the spring is the most important component of the drive adjustment structure. To ensure the effective operation of the spring, flange edges 19 are extended on the outer sides of the impact pin 11 and the ejector pad 15 to limit the foot spring 12 and the clamping spring 16, so that the force received by the impact pin 11 and the ejector pad 15 can be transmitted to the spring, so that both are compressed. After the gas cylinder 3 is replaced, the drone takes off again. At this time, the drone body 1 no longer applies pressure to the foot support 7. The foot spring 12 and the clamping spring 16 quickly stretch and reset, causing the impact pin 11 and the ejector pad 15 to move downward. The downward movement of the ejector pad 15 causes the clamping rod 14 to move downward, which in turn causes the gas cylinder 3 clamping structure to tighten the newly installed gas cylinder 3, completing the limit.

[0046] Example 7

[0047] like Figures 1 to 6The drone landing pad shown includes a gas cylinder 3 clamping structure connected between vertically movable clamping rods 14. Under normal conditions, the gas cylinder 3 clamping structure limits the position of the gas cylinder 3. When the clamping rods 14 move upwards, the gas cylinder 3 clamping structure disengages, creating a gap between the gas cylinder 3 and the drone body 1, facilitating the removal of the gas cylinder 3 from the gap. The gas cylinder 3 clamping structure can be any of the following: a limiting strap 26, a limiting guide wheel, a limiting fulcrum, a pin, or a latch, allowing it to disengage during upward movement.

[0048] In this invention, the gas cylinder 3 clamping structure is configured as a bearing seat 25 and a strap 26. The strap 26 connects the two bearing seats 25 on the same side. When taut, the strap 26 limits the gas cylinder 3, preventing it from falling and providing power for the drone's normal flight. However, since the clamping rod 14 is only slidably mounted on the tower top plug 9 via an O-ring seal 17, it's impossible to control the rotation of the clamping rod 14 during vertical movement. When the clamping rod 14 rotates horizontally, it causes the strap 26 to rotate via the bearing seat 25, resulting in the strap 26 not being fully secured to the gas cylinder 3. This allows the gas cylinder 3 to easily slip out, affecting the drone's normal flight operation. Therefore, after determining the optimal limiting state of the strap 26, a guide block 23 is added to the ejector pad at the bottom of the clamping rod 14. Correspondingly, a guide rail 22 is provided at the same position on the fixed mounting sleeve 5. The guide block 23 slides on the guide rail 22, achieving relative limiting. In this way, when the clamping rod 14 moves up and down to loosen and tighten the clamping structure of the gas cylinder 3, it will drive the guide block 23 on the ejector pad to move linearly on the guide rail 22, which will then drive the clamping rod 14 to clamp in the correct direction, thus preventing the strap 26 from deflecting and ensuring that the clamping structure of the gas cylinder 3 operates in the best condition.

[0049] Example 8

[0050] like Figures 1 to 6The UAV landing pad shown has O-rings 17 on both the adjusting inner sleeve 6 and the top plug 9. The O-rings 17 are in frictional contact with the foot bracket 7 and the clamping rod 14, respectively. It is known that the clamping rod 14 initially maintains a sealed state with the top plug 9 via the O-rings 17, i.e., with the fixed mounting sleeve 5. After the adjusting inner sleeve 6 and the foot bracket 7 are installed, the foot bracket 7 will maintain a sealed state with the adjusting inner sleeve 6 via the O-rings 17. In this way, a brief vacuum will be formed inside the entire adjusting inner sleeve 6. Under vacuum, the object will become difficult to move due to air resistance. Consequently, the spring may not receive enough force to loosen the clamping structure of the gas cylinder 3. Therefore, two air pressure balance holes 27 are provided on the footplate plug 8 to accelerate air circulation and reduce air resistance. This allows the impact pin 11 to easily push open the ejector pad when the drone lands, thereby opening the clamping structure of the gas cylinder 3 and allowing the gas cylinder 3 to be removed from the drone body 1, reducing the cost of manual replacement and maintenance.

[0051] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0052] The above description is only used to illustrate the technical solution of the present invention and is not intended to limit it. Any other modifications or equivalent substitutions made by those skilled in the art to the technical solution of the present invention, as long as they do not depart from the spirit and scope of the technical solution of the present invention, should be covered within the scope of the claims of the present invention.

Claims

1. A landing buffer for a drone, comprising a drone fuselage (1), a rotor (2), and a gas cylinder (3), characterized in that, The bottom of the drone fuselage (1) is provided with multiple tripod sleeves (4). A fixed mounting sleeve (5) is installed inside the tripod sleeve (4). An adjusting inner sleeve (6) is installed inside the fixed mounting sleeve (5). A foot bracket (7) is slidably installed inside the adjusting inner sleeve (6). A tripod plug (8) and a tower top plug (9) are provided inside the fixed mounting sleeve (5). A first sliding hole (10) is opened on the tripod plug (8). A firing pin (11) is slidably installed inside the first sliding hole (10). A foot spring (12) is connected between the striker (11) and the foot plug (8). A second sliding hole (13) is opened on the tower top plug (9). A clamping rod (14) is slidably provided in the second sliding hole (13). A push-out pad (15) is provided at the bottom of the clamping rod (14). A clamping spring (16) is connected between the push-out pad (15) and the tower top plug (9). Flange edges (19) are extended on the outer sides of both the striker (11) and the push-out pad (15).

2. The unmanned aerial vehicle (UAV) landing pad according to claim 1, characterized in that, The adjusting inner sleeve (6) passes through the leg sleeve (4).

3. The unmanned aerial vehicle (UAV) landing pad according to claim 1, characterized in that, The inner sleeve (6) and the top plug (9) are both equipped with O-rings (17), and the O-rings (17) are in frictional contact with the foot bracket (7) and the clamping rod (14) respectively.

4. The unmanned aerial vehicle (UAV) landing pad according to claim 1, characterized in that, The adjusting inner sleeve (6) is screwed into the fixed mounting sleeve (5) via a threaded assembly (18).

5. A UAV landing buffer frame according to claim 1, characterized in that, The fixed installation sleeve (5) has a partition (20) in the middle, and a through hole (21) is opened on the partition (20).

6. A UAV landing buffer frame according to claim 5, characterized in that, The tripod plug (8) is located below the partition (20), and the ejector pad (15) is located above the partition (20).

7. The unmanned aerial vehicle (UAV) landing pad according to claim 1, characterized in that, The fixed mounting sleeve (5) has a guide rail (22), and a guide block (23) is provided on the left side of the flange edge (19) located on the ejector pad (15).

8. A UAV landing buffer frame according to claim 1, characterized in that, A gas cylinder clamping mechanism (24) is provided between the tops of the clamping rods (14). The gas cylinder clamping mechanism (24) includes a bearing seat (25) and a strap (26). A strap (26) is connected between every two bearing seats (25).

9. A UAV landing buffer frame according to claim 1, characterized in that, The tripod plug (8) has two air pressure balance holes (27).

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