Unmanned aerial vehicle landing cushioning device

Abstract

The application provides a UAV landing buffer device, which comprises a fuselage connecting seat, a supporting leg assembly, a landing bearing plate and a buffer mechanism; the fuselage connecting seat is fixedly arranged at the bottom of a UAV body; the supporting leg assembly comprises two supporting legs arranged in an inclined manner; the upper end of each supporting leg is fixedly connected with the fuselage connecting seat; the lower end of each supporting leg is connected with the landing bearing plate through the buffer mechanism; the buffer mechanism is fixedly arranged at the upper central position of the landing bearing plate; the buffer mechanism comprises a hollow elastic ring, a solid connecting block and a connecting column; the hollow elastic ring is bonded at the mounting groove arranged at the upper central position of the landing bearing plate; the upper end of the hollow elastic ring is connected with the solid connecting block; the upper end of the solid connecting block is provided with the connecting column; the hollow elastic ring, the solid connecting block and the connecting column are integrally formed; and the connecting column is detachably connected in the connecting hole arranged at the lower end of the supporting leg. The application has the advantages of simple structure, the ability to relieve the impact when the UAV lands, improved landing stability and improved safety of the body structure.

Description

Technical Field

[0001] This application relates to the field of buffer device technology, and in particular to a drone landing buffer device. Background Technology

[0002] With the widespread application of drones in aerial photography, logistics transportation, topographic mapping, inspection and monitoring, and other fields, the complexity of their operating environments and tasks is constantly increasing. After completing flight missions, drones need to take off and land frequently. The impact load during landing directly acts on the airframe structure. If the cushioning design is inadequate, it can easily cause deformation of the support legs, loosening of fuselage connections, and even instability of the aircraft's attitude. Therefore, the landing cushioning structure of drones has gradually become one of the key technologies affecting the airframe's lifespan and safety. Existing cushioning designs mainly focus on the lightweighting, impact resistance, and maintainability of the fuselage support structure, but a balance between structural simplification and cushioning performance remains difficult to achieve.

[0003] Currently, common drone cushioning structures typically employ two methods: first, rubber or foam pads are placed at the bottom of the support legs to absorb impact energy through material elasticity; second, springs, sliding rods, or airbag-type cushioning mechanisms are installed inside the support legs to absorb energy through mechanical deformation upon landing. The former has a simple structure but limited cushioning stroke, and the rubber pads are prone to fatigue and aging, resulting in decreased cushioning performance; while the latter provides a larger deformation space, its complex structure and numerous parts increase the weight and assembly difficulty of the drone, and long-term use can easily lead to jamming and sealing failure.

[0004] In summary, existing UAV landing cushioning systems generally suffer from drawbacks such as complex structure, heavy weight, and unstable cushioning transmission paths. Particularly in small or medium-sized UAVs, the connections between the fuselage connector, support legs, and load-bearing components are often rigid, lacking effective energy absorption mechanisms. This results in concentrated energy transfer to the fuselage upon landing, easily causing structural vibration and localized damage. Therefore, designing a simple, lightweight UAV landing cushioning device with effective cushioning and energy dispersion capabilities has become a critical problem that urgently needs to be solved by those skilled in the art. Utility Model Content

[0005] This application provides a drone landing buffer device to solve the problems of insufficient buffering performance during drone landing, direct transfer of impact energy to the fuselage, and damage to the fuselage structure.

[0006] This application provides a drone landing buffer device, including a fuselage connecting seat, a support leg assembly, a landing bearing plate, and a buffer mechanism; The fuselage connecting seat is fixedly installed at the bottom of the UAV body. The support leg assembly includes two inclined support legs. The upper ends of the two support legs are fixedly connected to the bottom sides of the fuselage connecting seat, and the lower ends extend to the bottom of the UAV body and are connected to the buffer mechanism. The lower ends of the two support legs are connected to the landing bearing plate through the buffer mechanism. The buffer mechanism is fixedly installed at the upper center of the landing bearing plate. The buffer mechanism includes a hollow elastic ring bonded to the mounting groove at the upper center of the landing bearing plate, a solid connecting block connected to the upper end of the hollow elastic ring, and a connecting post installed at the upper end of the solid connecting block. The hollow elastic ring, the solid connecting block, and the connecting post are integrally formed. The connecting post is detachably connected to the connecting hole at the lower end of the support leg.

[0007] In one optional embodiment, the landing load plate is an integrally bent strip-shaped load plate body. The landing load plate includes a bottom plate portion located below and a triangular reinforcing portion disposed above the bottom plate portion and formed by the intersection of two opposing bent plates. The two bent plate portions of the triangular reinforcing portion extend upward to form straight edge flanges perpendicular to the bottom plate portion. The middle part of the landing load plate is provided with a mounting groove for installing the buffer mechanism. The lower surface of the landing load plate is provided with three raised grounding blocks spaced apart along the length direction.

[0008] In one optional embodiment, the fuselage connecting seat includes an upper fixing plate and a lower bearing plate, which are fixedly connected by two vertically arranged connecting ribs to form an integral frame structure. The upper fixing plate is used to fix it to the bottom of the drone body, and the lower bearing plate is provided with support leg mounting seats on both sides of the lower part for fixing the upper end of the support leg.

[0009] In one optional embodiment, the hollow elastic ring is a closed annular cavity with a cross-section that is circular or approximately circular, the ratio of its inner diameter to its outer diameter being 0.55 to 0.85, and the circumferential wall thickness of the hollow elastic ring being 2 to 6 mm.

[0010] In one alternative embodiment, the cushioning mechanism is made of thermoplastic elastomer or silicone rubber.

[0011] In one alternative embodiment, the two support legs are tilted at an angle of 30° to 60° relative to the fuselage connecting seat.

[0012] In one alternative embodiment, the landing bearing plate is integrally formed from aluminum alloy or magnesium-aluminum alloy material.

[0013] Compared with the prior art, this application has the following beneficial effects: 1. This application provides a landing cushioning device for unmanned aerial vehicles (UAVs). The landing support plate is positioned at the bottom of the entire device, making initial contact with the ground during UAV descent. The reaction force from the ground on the support plate is transmitted through the plate to the cushioning mechanism fixed to it, and then through the respective connected support legs to the fuselage connecting seat. This bottom-up load transmission process makes the cushioning mechanism an elastic buffer node in the support system, forming a flexible transition area between the rigid structure and the fuselage. The cushioning mechanism is located at the center above the landing support plate, with two sets of cushioning mechanisms connected to the lower ends of their respective support legs, ensuring that each support leg has independent energy absorption capacity under load. This arrangement helps reduce the localized impact caused by one side contacting the ground first upon landing, resulting in a more stable overall stress distribution on the lower part of the fuselage.

[0014] 2. The buffer mechanism of this application consists of a hollow elastic ring bonded and fixed in a mounting groove on the landing bearing plate, a solid connecting block integrally connected above it, and an upwardly extending connecting column. The hollow elastic ring undergoes axial compression during UAV landing and deforms under the constraint of the mounting groove to absorb part of the load; the solid connecting block acts as a transition and support, allowing the load to be primarily transmitted axially to the connecting column. Furthermore, the three components are integrally molded, reducing loosening and gap variations at the assembly interface. The overall structure forms a continuous load transfer process from the landing bearing plate through the buffer mechanism to the support legs and fuselage connecting seat, allowing the impact load to gradually transition and be dispersed between structures, thereby reducing stress concentration in the bottom connection area of ​​the fuselage and contributing to improved landing stability and durability of the connection parts.

[0015] 3. The fuselage connector of this application is fixedly installed at the bottom of the UAV body to connect the body to the supporting leg assembly below. During UAV landing, the reaction force from the supporting legs is gradually transmitted to the fuselage connector via the buffer mechanism. This connector plays a role in load distribution and structural fixation during the stress process. Its arrangement makes the bottom of the body a stress reference surface, allowing the load to be distributed more evenly to the body frame structure, avoiding localized stress concentration caused by single-point stress. The presence of the fuselage connector provides the buffer mechanism with relatively stable upper support conditions during operation, ensuring stable buffer stroke and more reliable energy absorption. This structural arrangement provides moderate rigidity between the UAV body and the supporting leg assembly, balancing structural strength and buffering performance during impact transmission, thereby improving the overall coordination and reliability of the device during landing. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of a drone landing buffer device provided in an embodiment of this application; Figure 2 This is a schematic diagram of the structure of a fuselage connector provided in one embodiment of this application; Figure 3 This is a schematic diagram illustrating the connection between the fuselage connecting base and the support leg assembly according to an embodiment of this application; Figure 4 This is a schematic diagram showing the connection between the support leg and the landing bearing plate according to an embodiment of this application; Figure 5 This is a schematic diagram of the landing support plate provided in one embodiment of this application.

[0018] Explanation of reference numerals in the attached figures: 10-Unmanned aerial vehicle (UAV) airframe; 100-Body connecting base; 101-Upper fixing plate; 102-Lower bearing plate; 103-Connecting rib plate; 104-Support leg mounting base; 200 - Support leg assembly; 210 - Support leg; 300 - Landing bearing plate; 301 - Base plate; 302 - Triangular reinforcement; 3021 - Straight edge flange; 310 - Mounting groove; 320 - Raised grounding block; 400 - Buffer mechanism; 410 - Hollow elastic ring; 420 - Solid connecting block; 430 - Connecting column. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions in the embodiments of this application are described clearly and completely below. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are also within the scope of protection of this application.

[0020] like Figures 1-5 As shown in the figure, this application provides a drone landing buffer device, including a fuselage connecting seat 100, a support leg assembly 200, a landing bearing plate 300 and a buffer mechanism 400.

[0021] The fuselage connector 100 is fixedly mounted on the bottom of the UAV body 10. The support leg assembly 200 includes two inclined support legs 210. The upper ends of the two support legs 210 are fixedly connected to the bottom sides of the fuselage connector 100, and the lower ends extend to the bottom of the UAV body and are connected to a buffer mechanism 400. The lower ends of the two support legs 210 are connected to a landing bearing plate 300 through the buffer mechanism 400, which is fixedly mounted on the upper part of the landing bearing plate 300. The centrally located buffer mechanism 400 includes a hollow elastic ring 410 bonded to a mounting groove 310 at the center of the upper part of the landing bearing plate 300, a solid connecting block 420 connected to the upper end of the hollow elastic ring 410, and a connecting post 430 located on the upper end of the solid connecting block 420. The hollow elastic ring 410, the solid connecting block 420, and the connecting post 430 are integrally formed. The connecting post 430 is detachably connected to a connecting hole at the lower end of the support leg 210. Optionally, the connecting post 430 and the connecting hole at the lower end of the support leg 210 are connected by a coaxial insertion method. The outer diameter of the connecting post 430 and the inner diameter of the connecting hole of the support leg 210 are in clearance or slight interference fit, and can be locked by through screws, pins, or lateral locking screws to prevent loosening or detachment under repeated landing loads. This connection method is easy to assemble and facilitates the replacement of the buffer mechanism 400 later, while maintaining connection strength and assembly stability, making it suitable for the frequent take-off and landing environment of UAVs.

[0022] In the specific design of installing the buffer mechanism 400 using the landing bearing plate 300, the width of the mounting groove 310 is matched with the outer diameter of the hollow elastic ring 410. To improve bonding reliability, the inner wall of the landing bearing plate 310 can be roughened or cleaned before bonding, and a primer layer can be applied to improve interfacial adhesion. The bonding material can be acrylic structural adhesive or silicone-based structural adhesive, which is cured at room temperature or under heating conditions. Through the above methods, the hollow elastic ring 410 can be stably embedded in the mounting groove 310, thereby ensuring that the buffer mechanism 400 has reliable connection strength and reusability during repeated pressure processes.

[0023] In this embodiment, the landing bearing plate 300 is located at the lower part of the entire device, making initial contact with the ground during the drone's descent and landing. The reaction force from the ground on the bearing plate is transmitted through the bearing plate to the buffer mechanism 400 fixed thereon, and then through the respective connected support legs 210 to the fuselage connecting seat 100. This load transmission process from bottom to top makes the buffer mechanism an elastic buffer node in the support system, forming a flexible transition area between the rigid structure and the fuselage. The buffer mechanism 400 is located at the upper center of the landing bearing plate 300, and the two sets of buffer mechanisms are respectively connected to the lower ends of the corresponding support legs 210, so that each support leg has independent buffering and energy absorption capacity when under load. This arrangement helps to reduce the local impact caused by one side contacting the ground first when the device lands, thereby making the overall stress on the lower part of the fuselage more stable.

[0024] Meanwhile, the buffer mechanism 400 in this embodiment consists of a hollow elastic ring 410 bonded and fixed in the mounting groove 310 on the landing bearing plate 300, a solid connecting block 420 integrally connected above it, and an upwardly extending connecting column 430. The hollow elastic ring 410 undergoes axial compression during UAV landing and deforms under the constraint of the mounting groove 310 to absorb part of the load; the solid connecting block 420 acts as a transition and support, allowing the load to be primarily transmitted axially to the connecting column 430. Furthermore, the three components are integrally formed, reducing loosening and gap variations at the assembly interface. The overall structure forms a continuous load transfer process from the landing bearing plate through the buffer mechanism to the support leg and fuselage connecting seat 100, allowing the impact load to gradually transition and be dispersed between structures, thereby reducing stress concentration in the bottom connection area of ​​the fuselage and helping to improve the stability of UAV landing and the durability of the connection parts.

[0025] Furthermore, in this embodiment, the fuselage connector 100 is fixedly installed at the bottom of the UAV body 10 to connect the body to the supporting leg assembly 200 below. During UAV landing, the reaction force from the supporting leg 210 is gradually transmitted to the fuselage connector 100 via the buffer mechanism 400. This connector plays a role in load distribution and structural fixation during the stress process. Its arrangement makes the bottom of the body a stress reference surface, allowing the load to be distributed more evenly to the body frame structure, avoiding local stress concentration caused by single-point stress. With the presence of the fuselage connector 100, the buffer mechanism 400 can obtain more stable upper support conditions during operation, making the buffer stroke stable and the energy absorption effect more reliable. The arrangement of this structure makes the connection between the UAV body and the supporting leg assembly moderately rigid, balancing structural strength and buffer performance during impact transmission, thereby improving the overall coordination and reliability of the device during landing.

[0026] In some embodiments, the landing bearing plate 300 is an integrally bent strip bearing plate body. The landing bearing plate 300 includes a bottom plate portion 301 located below and a triangular reinforcing portion 302 disposed above the bottom plate portion 301 and formed by the intersection of two opposing bent plates. The two bent plate portions of the triangular reinforcing portion 302 extend upward to form straight edge flanges 3021 perpendicular to the bottom plate portion 301. The middle part of the landing bearing plate 300 is provided with a mounting groove 310 for mounting a buffer mechanism 400. The lower surface of the landing bearing plate 300 is provided with three protruding grounding blocks 320 spaced apart along the length direction.

[0027] In this embodiment, the landing bearing plate 300 adopts an integrally bent structure, with a triangular reinforcing portion 302 formed by the intersection of two opposing inclined bent plates on its upper part. When bearing loads from the buffer mechanism 400, this structure can make the load form a relatively dispersed force line distribution inside the plate, reducing the pressure on the bottom plate 301. Moreover, the configuration of the triangular reinforcing portion 302 makes the plate less prone to overall bending deformation after being subjected to force, thereby improving the structural stability of the bearing plate. In addition, the straight-edge flange 3021 extending from the upper part of the triangular reinforcing portion 302 can provide a certain lateral support during landing, so that the plate can still maintain its overall shape stability well in the presence of lateral disturbances or poor ground contact. Through this structural form combining bending and flanges, the landing bearing plate 300 has a higher resistance to deformation during UAV landing impact. Furthermore, in this embodiment, three raised grounding blocks 320 are spaced apart along the length of the lower surface of the landing bearing plate 300. During the landing of the UAV, these blocks can disperse the ground reaction force, reduce single-point contact pressure, and provide protection for the landing bearing plate 300. Optionally, rubber pads are provided at the bottom of the three raised grounding blocks 320.

[0028] In some embodiments, the fuselage connecting base 100 includes an upper fixing plate 101 and a lower bearing plate 102, which are fixedly connected by two vertically arranged connecting ribs 103 to form an integral frame structure. The upper fixing plate 101 is used to fix and connect to the bottom of the UAV body 10, and the lower bearing plate 102 has support leg mounting seats 104 on both sides of the lower part for fixing the upper end of the support leg 210.

[0029] Optionally, the upper fixing plate 101 of the fuselage connector 100 is fixedly installed on the bottom of the UAV body 10 by screws or riveting. Alternatively, it can be fixed by structural adhesive or a combination of screws and adhesive, depending on structural requirements. For ease of installation, the upper fixing plate 101 has pre-drilled mounting holes corresponding to the connection holes on the bottom of the fuselage. The fuselage connector 100 is preferably made of aluminum alloy or stainless steel sheet with a thickness ranging from 1.0 to 3.0 mm to ensure connection strength while also meeting lightweight requirements. This connection method facilitates assembly and disassembly, maintains a stable fixed state under multiple takeoff and landing conditions, and reduces the risk of structural fatigue.

[0030] In the above embodiment, the fuselage connecting base 100 includes an upper fixed plate 101, a lower bearing plate 102, and two vertically arranged connecting ribs 103, which are fixedly connected to form an integrated frame structure. When under stress, the upper and lower plates support each other through the ribs, enabling the fuselage connecting base 100 to maintain a stable geometric shape when bearing loads from the support legs 210. The connecting ribs 103 reinforce and constrain the upper and lower plates, helping to reduce deformation and improve overall structural rigidity. Compared to a single-layer plate connection structure, this frame form with upper and lower plates and ribs improves bending and torsional resistance with only a slight increase in weight, making it suitable for the repeated takeoff and landing environments of UAVs.

[0031] Furthermore, in this embodiment, support leg mounting seats 104 are provided on both sides of the lower part of the lower support plate 102 for fixed connection with the support leg 210. Specifically, the support leg mounting seat 104 is provided with through holes for installing locking parts (such as locking bolts) that are inserted and fixed to the upper end of the support leg 210. The support leg mounting seat 104 and the lower support plate 102 are integral structures. This structural arrangement helps to evenly distribute the load from the buffer mechanism 400 to the fuselage connecting seat 100 when the UAV lands, thereby improving the reliability of the UAV under multiple landing conditions.

[0032] In some embodiments, the hollow elastic ring 410 is a closed annular cavity with a circular or nearly circular cross-section. The ratio of its inner diameter to its outer diameter is 0.55 to 0.85, and the circumferential wall thickness of the hollow elastic ring 410 is 2 to 6 mm. This structure can generate relatively uniform deformation in the circumferential direction of the ring wall when the buffer mechanism 400 is compressed. The compression of the internal cavity increases the overall elastic stroke, thereby helping to absorb part of the impact load during landing. Furthermore, by limiting the ratio of the inner and outer diameters and the range of the wall thickness of the hollow elastic ring 410, this embodiment ensures that the hollow elastic ring 410 has sufficient deformation space while maintaining the required structural strength under load. When the landing bearing plate 300 is subjected to ground force and the load is transferred to the buffer mechanism 400, the hollow elastic ring undergoes elastic compression along the axial direction, which delays and disperses the impact load to a certain extent in time, thereby reducing the impact of the load being concentrated and transferred to the support leg 210 and the fuselage connecting seat 100 in an instant. Through this structural form, the buffer mechanism achieves a relatively stable energy absorption process while maintaining a compact shape, and plays an effective role in mitigating the impact of the UAV landing.

[0033] In some embodiments, the buffer mechanism 400 is made of thermoplastic elastomer or silicone rubber. These materials combine good elastic recovery performance and deformation durability, and can maintain a stable mechanical response after repeated compression deformation. In addition, these two types of materials have good molding properties and are suitable for integral injection molding or compression molding processes, so that the hollow elastic ring 410, the solid connecting block 420 and the connecting column 430 can be integrally molded.

[0034] In some embodiments, the tilt angle of the two support legs 210 relative to the fuselage connecting seat 100 is 30° to 60°. This angle setting is closely related to the landing attitude and support stability of the UAV. When the support legs are nearly vertical, the axial load-bearing capacity is strong, but the lateral anti-overturning performance is weak. If there are local undulations in the ground or wind interference, the aircraft is prone to lateral swaying. Conversely, when the support legs are excessively tilted, although the lateral support range increases, the bending stress of the support legs when bearing impact loads increases significantly, which can easily lead to structural fatigue over long-term use. In this embodiment, by controlling the tilt angle between 30° and 60°, the force on the support legs 210 in the vertical and horizontal directions can be more reasonably distributed, enabling the UAV to effectively disperse impact force and maintain a stable attitude upon landing.

[0035] In some embodiments, the landing load plate 300 is integrally formed from aluminum alloy or magnesium-aluminum alloy material.

[0036] In the above embodiments, the landing bearing plate 300 is integrally formed from aluminum alloy or magnesium-aluminum alloy. These metal materials have high specific strength and specific stiffness, which can significantly reduce the component's weight while ensuring load-bearing performance, meeting the structural requirements of UAVs for both lightweight and strength. Furthermore, aluminum alloy and magnesium-aluminum alloy have good ductility, allowing for the one-time forming of structural features such as the triangular reinforcement 302 and the straight-edge flange 3021 through bending or pressing processes, thereby achieving a high-rigidity structure without additional processing.

[0037] The drone landing buffer device provided in this embodiment can be manufactured and its components connected in accordance with conventional machining and assembly processes in the field. Components such as the buffer mechanism, landing bearing plate, and fuselage connecting seat can be assembled through molding, welding, bonding, or screwing. The device as a whole possesses good machining feasibility and structural stability. Based on the above structural configuration, the drone landing buffer device of this embodiment can be assembled and functionally realized under conventional manufacturing conditions, thus making it suitable for drone landing buffer scenarios.

[0038] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A drone landing buffer device, characterized in that, This includes the fuselage connecting base, support leg assembly, landing load plate, and cushioning mechanism; The fuselage connecting seat is fixedly installed at the bottom of the UAV body. The support leg assembly includes two inclined support legs. The upper ends of the two support legs are fixedly connected to the bottom sides of the fuselage connecting seat, and the lower ends extend to the bottom of the UAV body and are connected to the buffer mechanism. The lower ends of the two support legs are connected to the landing bearing plate through the buffer mechanism. The buffer mechanism is fixedly installed at the upper center of the landing bearing plate. The buffer mechanism includes a hollow elastic ring bonded to the mounting groove at the upper center of the landing bearing plate, a solid connecting block connected to the upper end of the hollow elastic ring, and a connecting post installed at the upper end of the solid connecting block. The hollow elastic ring, the solid connecting block, and the connecting post are integrally formed. The connecting post is detachably connected to the connecting hole at the lower end of the support leg.

2. The drone landing buffer device according to claim 1, characterized in that, The landing load plate is a strip-shaped load plate integrally bent. The landing load plate includes a bottom plate portion located below and a triangular reinforcing portion located above the bottom plate portion and formed by the intersection of two opposing bent plates. The two bent plate portions of the triangular reinforcing portion extend upward to form straight edge flanges perpendicular to the bottom plate portion. The middle part of the landing load plate is provided with a mounting groove for installing the buffer mechanism. Three raised grounding blocks are spaced apart along the length direction on the lower surface of the landing load plate.

3. The drone landing buffer device according to claim 1 or 2, characterized in that, The fuselage connecting seat includes an upper fixing plate and a lower bearing plate, which are fixedly connected by two vertically arranged connecting ribs to form an integrated frame structure. The upper fixing plate is used to fix it to the bottom of the drone body, and the lower bearing plate is provided with support leg mounting seats on both sides of the lower part for fixing the upper end of the support leg.

4. The drone landing buffer device according to claim 1, characterized in that, The hollow elastic ring is a closed annular cavity with a cross-section that is circular or approximately circular. The ratio of the inner diameter to the outer diameter is 0.55 to 0.85, and the circumferential wall thickness of the hollow elastic ring is 2 to 6 mm.

5. The drone landing buffer device according to claim 1, characterized in that, The cushioning mechanism is made of thermoplastic elastomer or silicone rubber.

6. The drone landing buffer device according to claim 1, characterized in that, The two support legs are tilted at an angle of 30° to 60° relative to the fuselage connecting seat.

7. The UAV landing buffer device according to claim 1 or 2, characterized in that, The landing bearing plate is integrally formed from aluminum alloy or magnesium-aluminum alloy materials.

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