Buffer device for drone landing

Abstract

The application discloses a buffer device for unmanned aerial vehicle landing, relates to the technical field of mandrel detection, and comprises an unmanned aerial vehicle body and fan blades. A buffer chassis is fixed to the bottom of the unmanned aerial vehicle body, and a buffer unit for unmanned aerial vehicle landing is fixed below the buffer chassis. The buffer unit is provided with multiple groups and is uniformly arranged in a matrix. Each group comprises two buffer units arranged in mirror image. The buffer unit is provided with multiple obliquely arranged supporting rod bodies. Adjacent two supporting rod bodies are rotationally connected through torsional springs, so that the length of the buffer unit can be adaptively adjusted to adapt to the landing of different height terrains. The buffer device can realize the technical effects of expanding the applicable environment range of landing, improving landing flexibility and improving landing stability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to a buffer device for landing of unmanned aerial vehicles. BACKGROUND

[0002] An unmanned aerial vehicle is a kind of aircraft that does not need to be directly controlled by a pilot, and can fly autonomously by means of pre-programmed flight plans or wireless control. It can perform diversified tasks according to requirements, and is commonly used in military, civilian and commercial fields. Among them, civilian unmanned aerial vehicles are commonly used in aerial photography, agriculture, plant protection, disaster relief and other fields.

[0003] For the landing of unmanned aerial vehicles, a buffer device for landing of unmanned aerial vehicles is disclosed in Chinese patent No. CN117284474B, which comprises a shock absorption mechanism, a slow descent mechanism and a buffer chassis. The shock absorption mechanism and the slow descent mechanism are both fixedly installed inside the buffer chassis. The number of shock absorption mechanisms is four. The shock absorption mechanisms are respectively fixedly installed around the four corners of the slow descent mechanism. The shock absorption mechanism comprises a foot shell. A gland is arranged inside the foot shell. A pressure spring is fixedly installed at the bottom of the gland. The invention uses a gas bag, a containing cavity and a jet shaft. The gas bag expands in the containing cavity. The airflow generated by the axial flow fan enters the jet shaft through the flow pipe. Then the gas is sprayed out. When the containing cavity is completely filled by the expansion of the gas bag, the unmanned aerial vehicle slowly falls. At the same time, the gas sprayed in the jet shaft reduces the buffer force when the unmanned aerial vehicle falls. The gas bag can better prevent the unmanned aerial vehicle from being damaged due to excessive impact force when landing.

[0004] The above-mentioned scheme improves the work efficiency to a certain extent when buffering the landing of unmanned aerial vehicles. However, in actual use, since the four shock absorption mechanisms of the above-mentioned scheme are only synchronized by fixed rods and sliding shafts, they are effective for landing on flat ground, but cannot independently and flexibly adjust the landing height in uneven terrain. The landing adaptation range is limited. If the ground height difference is large, some gas bags may not completely contact the ground, the support force of the foot frame is uneven, and the aircraft body may be tilted or even overturned. Moreover, when landing on uneven or inclined ground, the height difference of different contact points cannot be self-adapted, which causes the aircraft body to tilt and the landing process to be unstable. SUMMARY

[0005] The present application provides a buffer device for landing of unmanned aerial vehicles, which solves the technical problems of limited landing application environment range, low landing flexibility and low landing stability in the prior art, and achieves the technical effects of expanding the landing application environment range, improving the landing flexibility and improving the landing stability.

[0006] The present application provides a buffer device for landing of unmanned aerial vehicles, which comprises an unmanned aerial vehicle body and a fan blade. The bottom of the unmanned aerial vehicle body is fixed with a buffer chassis. A buffer unit for landing of unmanned aerial vehicles is fixed below the buffer chassis.

[0007] The buffer unit is provided with multiple groups and is arranged uniformly in a matrix, each group including two buffer units arranged in mirror image, the buffer unit having multiple support rods arranged in an inclined manner, and adjacent two support rods being connected by a torsion spring for adaptive adjustment of the length thereof to adapt to different height terrains.

[0008] Further, the buffer unit includes an L-shaped plate, a support rod and a foot support plate.

[0009] The L-shaped plate is fixed below the buffer chassis to provide a fixed base for the support rod, the support rod is provided with multiple support rods arranged at the bottom of the L-shaped plate, the support rod arranged above is connected to the horizontal section of the L-shaped plate, and adjacent two support rods are connected by a torsion spring, and the foot support plate is fixed at the bottom of the support rod arranged below to provide stable ground support.

[0010] Further, multiple support rods are combined to form a multi-section elastic telescopic structure, when the unmanned aerial vehicle body contacts the ground, each group of support rods is adapted to adjust the length thereof under the gravity of the unmanned aerial vehicle body and is telescopic according to the pressure of the contact point to maintain the balance of the body.

[0011] Further, the support rod includes a main rod and a secondary support rod.

[0012] The main rod is a thick diameter structure for telescopic movement and providing basic support stiffness, and the secondary support rod is a thin diameter structure uniformly wound on the outer wall of the main rod for providing lateral support for the main rod.

[0013] Further, the secondary support rod is provided with three groups, namely a secondary support rod one, a secondary support rod two and a secondary support rod three, which are wound on the outer side of the main rod at a helix angle of 45°, 0° and 90° respectively for providing lateral support force for the main rod.

[0014] Further, the secondary support rod one is wound on the outer side of the main rod at a helix angle of 45°, the secondary support rod two is provided with multiple secondary support rods extending in parallel along the axis of the main rod and fixed on the outer side of the main rod, and the secondary support rod three is provided with two secondary support rods arranged above and below for combining and connecting the secondary support rod one and the secondary support rod two into a ring-shaped rhombic grid structure and reinforcing the outer edge of the main rod, and the three groups of secondary support rods are connected by laser welding at the intersection to form a rhombic grid node.

[0015] Further, the buffer unit further includes an adjusting mechanism for controlling the tension of the rhombic grid structure combined by the secondary support rods, the adjusting mechanism including a cross slot, an electric sliding block and a protrusion.

[0016] The cross grooves are provided with multiple groups and are arranged on the outer surface of the main rod; the protrusions are provided with multiple groups and correspond to the cross grooves one by one, and are respectively connected in the corresponding cross grooves through the electric sliding blocks, for pulling the diamond-shaped net structure in a certain direction through movement, and then adjusting the tension of the diamond-shaped net structure.

[0017] Further, each group of the cross grooves comprises two cross grooves arranged in an up-down manner, and the left and right two groups of cross grooves are arranged in an up-down staggered manner, for adapting to the impact from different positions and directions, and then adjusting the impact resistance of different positions of the whole support rod body.

[0018] Further, multiple cameras are fixed in the middle of the bottom surface of the buffer base, for detecting the impact from different directions; the electric sliding blocks are moved and controlled through the external control system, the impact direction is detected through the cameras and the result is fed back to the external control system, and the external control system issues an instruction to move and control the electric sliding blocks at the corresponding positions.

[0019] Further, the top of the foot support plate is an iron structure, and the buffer base is provided with an electromagnet, in the initial state, when the electromagnet is powered on, the foot support plate drives the support rod body to contract under the magnetic attraction, and when landing, the electromagnet is powered off, the foot support plate is lowered under the action of gravity and drives the support rod body to relax naturally.

[0020] One or more technical solutions provided in the application have at least the following technical effects or advantages:

[0021] By arranging multiple buffer units, different ground contact points can be independently responded, the local height can be finely adjusted through the self-adaptive adjustment of the support rod body, and the body inclination is avoided; through the segmented elastic structure, the buffer unit can adjust the contact surface angle and the support height according to the ground undulation, and the height is adjusted and the terrain change is adapted, the balance landing ability of the unmanned aerial vehicle on the concave-convex terrain is improved, the technical problems of the limited landing applicable environment range, the low landing flexibility and the low landing stability in the prior art are effectively solved, and the technical effects of the expanded landing applicable environment range, the improved landing flexibility and the improved landing stability are achieved. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a whole structure diagram of the buffer device for the unmanned aerial vehicle landing.

[0023] Figure 2 It is a lateral perspective structure diagram of the buffer device for the unmanned aerial vehicle landing.

[0024] Figure 3 It is a perspective structure diagram of the buffer unit of the buffer device for the unmanned aerial vehicle landing.

[0025] Figure 4It is the stereogram of the supporting rod of the buffer device for unmanned aerial vehicle landing of the application.

[0026] Figure 5 It is the lateral stereogram of the main supporting rod and the auxiliary supporting rod of the buffer device for unmanned aerial vehicle landing of the application.

[0027] Figure 6 It is the transverse sectional view of the supporting rod of the buffer device for unmanned aerial vehicle landing of the application.

[0028] Figure 7 It is the longitudinal sectional view of the supporting rod of the buffer device for unmanned aerial vehicle landing of the application.

[0029] Figure 8 It is the state schematic diagram of the buffer device for unmanned aerial vehicle landing of the application when the protrusion is moved and the grid formed by the auxiliary supporting rod is pulled.

[0030] In the figure: 100, unmanned aerial vehicle body; 110, fan blade; 120, buffer chassis; 130, camera; 200, buffer unit; 210, L-shaped plate; 220, supporting rod body; 221, main rod; 230, foot supporting plate; 240, auxiliary supporting rod; 241, auxiliary supporting rod one; 242, auxiliary supporting rod two; 243, auxiliary supporting rod three; 250, adjusting mechanism; 251, cross slot; 252, electric sliding block; 253, protrusion. DETAILED DESCRIPTION

[0031] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the accompanying drawings, in which preferred embodiments of the application are shown; however, the application can be realized in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and fully convey the scope of the application to those skilled in the art.

[0032] It should be noted that the terms "vertical", "horizontal", "upper", "lower", "left", "right", and similar expressions used herein are only for the purpose of illustration and do not represent the only embodiments.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the application belongs; the terms used herein in the specification are only for the purpose of describing the specific embodiments and are not intended to limit the application; the term "and / or" used herein includes any and all combinations of one or more related listed items.

[0034] Please refer to Figure 1Figure 1 is a schematic diagram of the overall structure of the unmanned aerial vehicle landing buffer device of the present application; the unmanned aerial vehicle landing buffer device of the present application can independently respond to different ground contact points by setting multiple buffer units 200, can realize "local fine tuning" through self-adaptive adjustment of the support rod body 220, and can avoid body tilting; through the segmented elastic structure, the buffer unit 200 can autonomously adjust the contact surface angle and support height according to the ground undulation, can autonomously adjust the height, can keep the body horizontal, can adapt to terrain changes, can reduce the risk of tilting, and can improve the balanced landing ability of the unmanned aerial vehicle on the concave-convex terrain; the technical effects of expanding the landing applicable environment range, improving the landing flexibility, and improving the stability during landing are realized.

[0035] Embodiment one: as shown in the figure, the unmanned aerial vehicle landing buffer device of the present application comprises an unmanned aerial vehicle body 100 and a fan blade 110, the bottom of the unmanned aerial vehicle body 100 is fixed with a buffer chassis 120, and the buffer chassis 120 is fixed below with a buffer unit 200 for unmanned aerial vehicle landing. Figures 1 to 3

[0036] The buffer unit 200 is provided with multiple groups and is uniformly arranged in a matrix, each group comprises two buffer units 200 arranged in mirror image, the buffer unit 200 is provided with multiple obliquely arranged support rod bodies 220, and the two adjacent support rod bodies 220 are rotationally connected through a torsion spring for self-adaptive adjustment of the length to adapt to the landing of different height terrains.

[0037] The buffer unit 200 comprises an L-shaped plate 210, a support rod body 220, and a foot support plate 230.

[0038] The L-shaped plate 210 is fixed below the buffer chassis 120 to provide a fixed basis for the support rod body 220; the support rod body 220 is provided with multiple support rod bodies 220 arranged at the bottom of the L-shaped plate 210, the support rod body 220 located above is rotationally connected to the horizontal section of the L-shaped plate 210, and the two adjacent support rod bodies 220 are rotationally connected through a torsion spring; the foot support plate 230 is fixed at the bottom of the support rod body 220 located below to provide stable ground support.

[0039] The multiple support rod bodies 220 are combined to form a multi-segmented elastic telescopic structure, when the unmanned aerial vehicle body 100 contacts the ground, each group of support rod bodies 220 is self-adaptively adjusted in length and is telescoped according to the pressure of the contact point under the gravity of the unmanned aerial vehicle body 100 itself to keep the body balanced.

[0040] The top of the foot support plate 230 is an iron structure, the bottom of the buffer chassis 120 is provided with an electromagnet, in the initial state, when the electromagnet is powered on, the foot support plate 230 drives the support rod body 220 to contract under the magnetic attraction, and when landing, the electromagnet is powered off, the foot support plate 230 is lowered under the action of gravity and drives the support rod body 220 to naturally relax.

[0041] ​The electromagnet is used for controlling the contraction and relaxation of the foot supporting plate 230 and the supporting rod body 220, which is a prior art and will not be described here.

[0042] In actual operation, the steps of the embodiment are as follows: first, when the unmanned aerial vehicle body 100 flies to the predetermined landing area, the electromagnet is powered off, the foot supporting plate 230 is lowered under the action of gravity and drives the supporting rod body 220 to relax naturally, at this time, the buffer unit 200 is in a natural relaxation state; then, when the unmanned aerial vehicle starts to contact the ground, the buffer unit 200 is slowly lowered under the action of gravity, and the plurality of supporting rod bodies 220 groups adapt to the landing terrain and are independently compressed until the unmanned aerial vehicle body 100 remains in a horizontal state and lands stably on the ground.

[0043] The technical solutions in the above embodiment have at least the following technical effects or advantages:

[0044] The buffer unit 200 with uniform distribution can independently respond to different ground contact points, and the supporting rod body 220 can realize “local fine adjustment” through self-adaptive adjustment, so as to avoid body tilting; the supporting rod body 220 is connected through a torsional spring to form a segmented elastic structure, so that the buffer unit 200 can absorb impact energy step by step under the action of gravity, avoiding single-point overload; and the L-shaped plate 210 elastically fixes the supporting rod body 220, and the anti-skid design of the foot supporting plate 230 can disperse impact force, so that the two form a “two-stage buffer system” to improve the buffer effect; each group of buffer units 200 can adjust the contact surface angle and support height according to the ground undulation, and automatically adjust the height to keep the body horizontal, adapt to terrain changes, reduce the risk of tilting, and at the same time, the structure is simpler and more reliable, which can improve the balanced landing ability of the unmanned aerial vehicle on the concave-convex terrain.

[0045] Embodiment two: when the supporting rod body 220 contacts a slope or a protruding object, the main rod 221 at different angles may be deformed differently when the supporting rod body 220 at different positions is subjected to pressure during bending and folding, and the single-axis telescopic main rod 221 is prone to lateral deformation instability, resulting in twisting or collapse of the main rod 221 when tilted, and the present application proposes the following technical solutions to solve the above technical problems, specifically:

[0046] As shown in Figure 3 and Figure 4 , the supporting rod body 220 includes a main rod 221 and a vice supporting rod 240;

[0047] The main rod 221 is a thick diameter structure for responsible for telescopic movement and providing basic support stiffness; the vice supporting rod 240 is a thin diameter structure, which is uniformly wound on the outer wall of the main rod 221, for providing lateral support for the main rod 221.

[0048] The main rod 221 is made of high-strength aluminum alloy, which has good strength and good corrosion resistance. The auxiliary support rods 240 are all made of spring steel, which has good toughness.

[0049] This application utilizes the coordinated operation of the main rod 221 and the secondary support rod 240. The secondary support rod 240, evenly wound along the length of the main rod 221, provides additional lateral support. This structural complementarity makes the entire support system more stable under lateral pressure, less prone to twisting or collapse. The presence of the secondary support rod 240 effectively increases the shear resistance of the support system. Therefore, during UAV landing, especially upon contact with slopes or protrusions, the support system may be subjected to lateral forces from different directions. The secondary support rod 240, through its evenly wound design, effectively disperses and resists these lateral forces, enhancing the bending stiffness of the main rod 221 and maintaining the overall stability of the support rod 220. This allows the UAV to land more smoothly, improving its safety and extending its service life.

[0050] Example 3: When the secondary support rod 240 is wound around the outside of the main rod 221 with a fixed spiral, it only optimizes lateral forces in a single direction. When multiple impacts occur simultaneously, the radial expansion of the secondary support rod 240 cannot uniformly cover all directions, resulting in insufficient local bending stiffness. To address the above-mentioned technical problems, this application proposes the following technical solution:

[0051] like Figures 3 to 7 As shown, the secondary support rod 240 is provided in three groups, namely secondary support rod one 241, secondary support rod two 242 and secondary support rod three 243, which are wound around the outside of the main rod 221 with helical angles of 45°, 0° and 90° respectively, to provide lateral support force for the main rod 221.

[0052] The first auxiliary support rod 241 is wound around the outside of the main rod 221 at a 45° helical angle; multiple second auxiliary support rods 242 are provided, all extending parallel to the axis of the main rod 221 and fixed to the outside of the main rod 221; two third auxiliary support rods 243 are provided and arranged vertically to combine and connect the first auxiliary support rod 241 and the second auxiliary support rod 242 into a ring-shaped diamond mesh structure and to reinforce the outer edge of the main rod 221; the three sets of auxiliary support rods 240 form a diamond mesh node at the intersection by laser welding.

[0053] The diamond-shaped mesh nodes formed by laser welding have excellent fatigue resistance, further enhancing the overall structure of the support system. During long-term use, these nodes can maintain a stable connection. These nodes not only fix the position of the secondary support 240, but also disperse stress through the mesh shape, making the support system more stable when facing complex stress conditions and less prone to loosening or breakage.

[0054] The present application forms a three-dimensional spiral reinforcing structure by setting three groups of vice supporting rods 240 and winding them outside the main rod 221 at different spiral angles. This structure not only increases the radial stiffness of the supporting rod system, but also improves its torsional resistance. Therefore, when contacting slopes or protrusions, the spiral vice supporting rods 240 and the diamond mesh nodes can provide additional lateral support force for the main rod 221, which effectively prevents the twisting or collapse of the main rod 221, thereby maintaining the balance and stability of the UAV. In particular, the circumferential annular winding of the 90° group of vice supporting rods 243 provides additional circumferential constraints for the supporting rod system, effectively preventing lateral deformation of the main rod 221.

[0055] At the same time, the spiral winding of the vice supporting rods 240 and the diamond mesh nodes enables stress to be more evenly distributed throughout the supporting rod system, effectively reducing stress concentration and improving the durability and reliability of the supporting rod system. Moreover, during the landing of the UAV, the supporting rod system will be subjected to impact and vibration from the ground, and the spiral vice supporting rods 240 and the diamond mesh nodes can absorb and alleviate these impacts and vibrations, thereby protecting the UAV body 100 from damage and enabling the UAV to maintain body balance more stably and reliably when landing on complex terrain.

[0056] Embodiment Four: In order to further improve the stability of the UAV landing and flexibly adapt to impacts from different directions, the present application proposes the following technical solutions to solve the above technical problems, specifically:

[0057] As shown in Figures 4 to 8 The buffer unit 200 further includes an adjusting mechanism 250 for controlling the tension of the diamond mesh structure composed of the vice supporting rods 240, and the adjusting mechanism 250 includes a cross slot 251, an electric sliding block 252, and a protrusion 253.

[0058] The cross slot 251 is provided with multiple groups, each of which is formed on the outer surface of the main rod 221. The protrusion 253 is provided with multiple groups, corresponding to the cross slot 251 one by one, and is slidably connected in the corresponding cross slot 251 through the electric sliding block 252, for pulling the diamond mesh structure in a certain direction by moving, thereby adjusting the tension thereof.

[0059] Each group of cross slots 251 includes two cross slots 251 arranged above and below, and the left and right adjacent two groups of cross slots 251 are arranged above and below in a staggered manner, for adapting to impacts from different positions and directions, thereby adjusting the impact resistance of different positions of the supporting rod body 220 as a whole.

[0060] The multiple cameras 130 are fixed in the middle of the bottom surface of the buffer chassis 120 and are used to detect impacts from different directions. The electric sliders 252 are controlled by an external control system. The direction of the impact is detected by the cameras 130 and the result is fed back to the external control system. The external control system then issues instructions to control the movement of the electric sliders 252 at the corresponding positions.

[0061] The external control system is used to control the movement of the electric sliders 252 at different positions, thereby pulling different positions of the mesh structure of the secondary support rods 240 and changing the tension. The preferred programmable logic controller is a prior art and will not be described here. The intelligent control of the buffer device is achieved by the cooperation of the adjustment mechanism 250 and the cameras 130. The cameras 130 can detect impacts from different directions in real time and feed the information back to the external control system. The control system then controls the movement of the electric sliders 252 according to the information, thereby achieving automatic adjustment and optimization of the buffer device.

[0062] In actual operation, when the unmanned aerial vehicle body 100 is falling, the cameras 130 monitor the ground terrain in real time. When the uneven or inclined ground is detected to be about to be contacted or the impact from a certain direction is detected, the cameras 130 transmit the terrain information to the external control system. Then, the external control system controls the electric sliders 252 in the corresponding direction to slide in the cross slot 251 according to the terrain information and external impact force, drives the movement of the protruding blocks 253, and then pulls the diamond mesh structure formed by the secondary support rods 240, changes the tension of the diamond mesh structure, and makes it adapt to the impact in a specific direction. Finally, after stable landing, the protruding blocks 253 return to the original position and the diamond mesh structure returns to its original state.

[0063] When the unmanned aerial vehicle is impacted, the main rod 221 may be deformed or have local stress concentration. The adjustment mechanism 250 can effectively disperse and relieve stress by changing the tension of the mesh structure formed by the secondary support rods 240, thereby avoiding damage to the main rod 221 due to excessive stress. Not only does it help to reduce the damage of the impact to the unmanned aerial vehicle, but also improves the overall durability of the device.

[0064] The application can control the position of the convex block 253 accurately through the sliding of the electric sliding block 252 in the cross groove 251, and then drive the diamond net structure connected by the auxiliary supporting rods 240 to pull in a specific direction. This adjusting mechanism can make the device adapt to the impact from different directions quickly, and improve the dynamic response capability and stability of the device. Through the cooperation of the electric sliding block 252 and the camera 130, when the camera 130 detects the impact from a certain direction, the external control system can control the electric sliding block 252 to drive the convex block 253 to move upwards or downwards or left or right, and then drive the diamond net structure connected by the plurality of auxiliary supporting rods 240 to pull in a certain direction (i.e. change the tension), so that the net structure formed by the outer auxiliary supporting rods 240 generates pulling and deformation in a certain direction, and then can adapt to the impact from different directions, and improve the local stress of the outer side of the main rod 221, to flexibly adjust the rigidity or tensile stress of different positions of the main rod 221, thereby improving the safety of the unmanned aerial vehicle, and enhancing the landing stability and safety of the unmanned aerial vehicle.

[0065] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A buffer device for unmanned aerial vehicle landing, comprising an unmanned aerial vehicle body (100) and a fan blade (110), wherein the bottom of the unmanned aerial vehicle body (100) is fixed with a buffer chassis (120), characterized in that, A buffer unit (200) for unmanned aerial vehicle landing is fixed below the buffer chassis (120); The buffer unit (200) is provided with multiple groups and is uniformly arranged in a matrix, each group including two buffer units (200) arranged in mirror image, the buffer unit (200) being provided with multiple tilt arranged support rod bodies (220), two adjacent support rod bodies (220) being connected through a torsion spring for self-adaptive adjustment of the length thereof to adapt to landing on different height terrains; The buffer unit (200) includes an L-shaped plate (210), a support rod body (220) and a foot support plate (230); The L-shaped plate (210) is fixed below the buffer chassis (120) to provide a fixed base for the support rod body (220); the support rod body (220) is provided with multiple support rod bodies (220) arranged at the bottom of the L-shaped plate (210), the support rod body (220) arranged above being connected to the horizontal section of the L-shaped plate (210) through a torsion spring; the foot support plate (230) is fixed at the bottom of the support rod body (220) arranged below to provide stable ground support; Multiple support rod bodies (220) are combined to form a multi-section elastic telescopic structure, when the unmanned aerial vehicle body (100) contacts the ground, each group of support rod bodies (220) is self-adaptive to adjust the length thereof under the gravity of the unmanned aerial vehicle body (100) and is telescopic according to the pressure of the contact point to keep the body balanced; The support rod body (220) includes a main rod (221) and a vice support rod (240); The main rod (221) is a thick diameter structure for telescopic movement and providing basic support stiffness; the vice support rod (240) is a thin diameter structure uniformly wound on the outer wall of the main rod (221) for providing lateral support for the main rod (221); The vice support rod (240) is provided with three groups, namely a vice support rod one (241), a vice support rod two (242) and a vice support rod three (243), and is wound on the outer side of the main rod (221) at a helix angle of 45°, 0° and 90° respectively for providing lateral support force for the main rod (221); The vice support rod one (241) is wound on the outer side of the main rod (221) at a helix angle of 45°; the vice support rod two (242) is provided with multiple vice support rods two (242) extending along the axis of the main rod (221) in parallel and fixed on the outer side of the main rod (221); the vice support rod three (243) is provided with two vice support rods three (243) arranged above and below for combining and connecting the vice support rod one (241) and the vice support rod two (242) into a ring type rhombic grid structure and reinforcing the outer edge of the main rod (221); the three groups of vice support rods (240) are connected through laser welding at the intersection to form a rhombic grid node. The buffer unit (200) further comprises an adjusting mechanism (250) for controlling the tension of the combined diamond grid structure of the auxiliary support rod (240), the adjusting mechanism (250) comprising a cross slot (251), an electric sliding block (252) and a protrusion (253); the cross slot (251) is provided with multiple groups and is arranged on the outer surface of the main rod (221); the protrusion (253) is provided with multiple groups and corresponds to the cross slot (251) one by one, and is slidably connected in the corresponding cross slot (251) through the electric sliding block (252), for pulling the diamond grid structure in a certain direction by moving, and then adjusting the tension thereof.

2. The unmanned aerial vehicle landing buffer apparatus of claim 1, wherein, Each group of the cross slot (251) comprises two cross slots (251) arranged in an up-down manner, and the left and right adjacent two groups of cross slots (251) are arranged in an up-down staggered manner, for adapting to the impact from different positions and directions, and then adjusting the anti-impact ability of different positions of the support rod body (220) as a whole. 3.The unmanned aerial vehicle landing buffer apparatus of claim 1, wherein A plurality of cameras (130) are fixed in the middle of the bottom surface of the buffer base plate (120), for detecting the impact from different directions; the electric sliding block (252) is moved and controlled by an external control system, the impact direction is detected by the camera (130) and the result is fed back to the external control system, and the electric sliding block (252) at the corresponding position is moved and controlled by the external control system according to the instruction. 4.The unmanned aerial vehicle landing buffer apparatus of claim 1, wherein, The top of the foot support plate (230) is an iron structure, and the bottom of the buffer base plate (120) is provided with an electromagnet; in the initial state, when the electromagnet is powered on, the foot support plate (230) drives the support rod body (220) to contract under the magnetic attraction, and when landing, the electromagnet is powered off, the foot support plate (230) is lowered under the action of gravity and drives the support rod body (220) to naturally relax.

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