Buffer device for landing of unmanned aerial vehicle

Abstract

The invention discloses a buffer device for landing of an unmanned aerial vehicle, and relates to the technical field of mandrel detection, the buffer device comprises an unmanned aerial vehicle body and fan blades, a buffer chassis is fixed at the bottom of the unmanned aerial vehicle body, and a buffer unit for landing of the unmanned aerial vehicle is fixed below the buffer chassis; a plurality of groups of buffer units are uniformly arranged in a matrix, each group comprises two buffer units which are arranged in a mirror image manner, each buffer unit is provided with a plurality of supporting rod bodies which are obliquely arranged, and every two adjacent supporting rod bodies are rotationally connected through a torsional spring and are used for adaptively adjusting the length of the supporting rod bodies so as to adapt to landing of terrains with different heights; the technical effects that the landing application environment range is expanded, the landing flexibility is improved, and the landing stability is improved can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a buffer device for unmanned aerial vehicle landing. Background Art

[0002] An unmanned aerial vehicle is an aircraft that does not require direct pilot control and flies autonomously through radio remote control or preset programs. It can perform diverse 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] Regarding the landing of unmanned aerial vehicles, a Chinese invention patent with the patent announcement number CN117284474B discloses a buffer device for unmanned aerial vehicle landing, including a shock absorption mechanism, a descent mechanism, and a buffer chassis. The shock absorption mechanism and the descent mechanism are both fixedly installed inside the buffer chassis. The number of shock absorption mechanisms is four, and the shock absorption mechanisms are respectively fixedly installed at the four corners around the descent mechanism. The shock absorption mechanism includes a support foot housing, and a gland is arranged inside the support foot housing. A bearing spring is fixedly installed at the bottom of the gland. Through structures such as an airbag, a receiving cavity, and a jet shaft, the airbag expands in the receiving cavity, and the airflow generated by the axial flow fan enters the jet shaft through the flow pipe and is then ejected. When the receiving cavity is completely filled by the expansion of the airbag, the unmanned aerial vehicle slowly descends. While descending, the gas ejected from the jet shaft reduces a part of the buffer force when the unmanned aerial vehicle descends, and the airbag better prevents the unmanned aerial vehicle from damaging the fuselage due to excessive impact force when landing.

[0004] When the above solution buffers the landing of an unmanned aerial vehicle, although the operation efficiency is improved to a certain extent, in actual use, since the four shock absorption mechanisms of the above solution only achieve synchronization through fixed rods and sliding shaft rods, it is effective for landing on flat ground, but in uneven terrain, the landing height cannot be independently and flexibly adjusted, and the landing adaptation range is limited. If the ground height difference is large, it may cause some airbags not to fully contact the ground, the support force of the landing gear is uneven, resulting in the inclination or even rollover of the fuselage. Moreover, when landing on uneven or inclined ground, it cannot adapt to the height difference of different contact points, resulting in the inclination of the fuselage and an unstable landing process. Summary of the Invention

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

[0006] The present application provides a buffer device for unmanned aerial vehicle landing, including an unmanned aerial vehicle fuselage and fan blades. A buffer chassis is fixed at the bottom of the unmanned aerial vehicle fuselage, and a buffer unit for unmanned aerial vehicle landing is fixed below the buffer chassis;

[0007] There are multiple groups of the buffer units, which are arranged uniformly in a matrix. Each group includes two mirror - arranged buffer units. The buffer unit is provided with a plurality of obliquely - arranged support rods, and adjacent two support rods are rotationally connected by torsion springs, which are used to adaptively adjust their own lengths to adapt to landings on terrains of different heights.

[0008] Furthermore, the buffer unit includes an L - shaped plate, support rods, and foot support plates;

[0009] The L - shaped plate is fixed under the buffer chassis, providing a fixed base for the support rods; a plurality of support rods are provided, all of which are arranged at the bottom of the L - shaped plate. The support rod located above is rotationally connected to the horizontal section of the L - shaped plate, and adjacent two support rods are rotationally connected by torsion springs; the foot support plate is fixed at the bottom of the support rod located below, which is used to provide stable ground support.

[0010] Furthermore, a plurality of the support rods are combined to form a multi - segment elastic telescopic structure. When the drone body touches the ground, each group of support rods, under the action of the landing gravity of the drone body itself, adaptively adjusts its own length and expands and contracts according to the pressure at the contact point to keep the body balanced.

[0011] Furthermore, the support rod includes a main rod and a sub - support rod;

[0012] The main rod is a thick - diameter structure, which is responsible for telescopic movement and provides basic support stiffness; the sub - support rod is a thin - diameter structure, which is evenly wound around the outer wall of the main rod and is used to provide lateral support for the main rod.

[0013] Furthermore, there are three groups of the sub - support rods, which are divided into sub - support rod one, sub - support rod two, and sub - support rod three, and are wound around the outer side of the main rod at spiral angles of 45°, 0°, and 90° respectively, which are used to provide lateral support force for the main rod.

[0014] Furthermore, the sub - support rod one is wound around the outer side of the main rod at a 45° spiral angle; there are a plurality of sub - support rod two, all of which extend parallel to the axis of the main rod and are fixed on the outer side of the main rod; there are two sub - support rod three, which are arranged up and down, and are used to combine and connect the sub - support rod one and the sub - support rod two into a surrounding diamond - shaped grid structure and reinforce the outer edge of the main rod; the three groups of the sub - support rods form diamond - shaped grid nodes by laser welding at the intersection points.

[0015] Furthermore, the buffer unit further includes an adjustment mechanism for controlling the tension of the diamond - shaped grid structure formed by the combination of the sub - support rods. The adjustment mechanism includes a cross - slot, an electric slider, and a convex block;

[0016] There are multiple groups of the cross grooves, which are all opened on the outer surface of the main rod; there are multiple groups of the bumps, which correspond to the cross grooves one by one, and are respectively slidably connected in the corresponding cross grooves through electric sliders, and are used to pull the diamond-shaped mesh structure in a certain direction by moving, so as to adjust its tension.

[0017] Further, each group of the cross grooves includes two cross grooves arranged up and down, and the left and right adjacent groups of cross grooves are arranged up and down staggeredly, so as to adapt to impacts from different positions and directions, and then adjust the impact resistance of different positions of the whole strut body.

[0018] Further, a plurality of cameras are fixed in the middle of the bottom surface of the buffer chassis, which are used to detect impacts from different directions; the electric slider is controlled to move through an external control system, the impact direction is detected by the camera and the result is fed back to the external control system, and the external control system issues an instruction to control the movement of the electric slider at the corresponding position.

[0019] Further, the top of the foot support plate is made of iron, and an electromagnet is arranged at the bottom of the buffer chassis. In the initial state, when the electromagnet is powered on, the foot support plate drives the strut body to contract under the magnetic attraction, and when landing, the electromagnet is powered off, and the foot support plate descends automatically under the action of gravity and drives the strut body to naturally expand.

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

[0021] By setting multiple buffer units, different ground contact points can be independently responded to, and "local height fine-tuning" can be realized through the adaptive adjustment of the strut body to avoid the tilting of the fuselage; through the segmented elastic structure, the buffer unit can independently adjust the contact surface angle and the support height according to the ground undulation, adjust the height by itself and adapt to the terrain change, improve the balance landing ability of the drone on the uneven terrain, effectively solve the technical problems of limited landing applicable environment range, low landing flexibility and low landing stability in the prior art, and achieve the technical effects of expanding the landing applicable environment range, improving the landing flexibility and improving the landing stability. Description of the Drawings

[0022] Figure 1 It is the overall structure diagram of the buffer device for the landing of the drone of the present invention.

[0023] Figure 2 It is the lateral three-dimensional structure diagram of the buffer device for the landing of the drone of the present invention.

[0024] Figure 3 It is the three-dimensional structure diagram of the buffer unit of the buffer device for the landing of the drone of the present invention.

[0025] Figure 4Stereoscopic structure diagram of the support rod of the buffer device for the landing of the UAV of the present invention.

[0026] Figure 5 Lateral stereoscopic structure diagram of the main support rod and the auxiliary support rod of the buffer device for the landing of the UAV of the present invention.

[0027] Figure 6 Transverse cross-sectional view of the support rod of the buffer device for the landing of the UAV of the present invention.

[0028] Figure 7 Longitudinal cross-sectional view of the support rod of the buffer device for the landing of the UAV of the present invention.

[0029] Figure 8 Schematic diagram of the state when the buffer device for the landing of the UAV of the present invention pulls the grid formed by the auxiliary support rod after the bump moves.

[0030] In the figure: 100, UAV fuselage; 110, fan blade; 120, buffer chassis; 130, camera; 200, buffer unit; 210, L-shaped plate; 220, support rod body; 221, main rod; 230, foot support plate; 240, auxiliary support rod; 241, first auxiliary support rod; 242, second auxiliary support rod; 243, third auxiliary support rod; 250, adjustment mechanism; 251, cross slot; 252, electric slider; 253, bump. Detailed implementation manners

[0031] To facilitate the understanding of the present invention, the present application will be described more comprehensively below with reference to the relevant attached drawings; the attached drawings show the preferred embodiments of the present invention. However, the present invention can be implemented in many different forms and is not limited to the embodiments described herein; on the contrary, these embodiments are provided to make the disclosure of the present invention more thorough and comprehensive.

[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 those skilled in the technical field to which the present invention belongs; the terms used in the description of the present invention in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present invention; the term "and / or" used herein includes any and all combinations of one or more of the related listed items.

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

[0035] Embodiment 1: As Figures 1 to 3 shown, the buffer device for the landing of the UAV of the present application includes a UAV fuselage 100 and a fan blade 110. A buffer chassis 120 is fixed to the bottom of the UAV fuselage 100, and a buffer unit 200 for the landing of the UAV is fixed below the buffer chassis 120;

[0036] A plurality of groups of the buffer units 200 are arranged in a matrix and evenly distributed. Each group includes two buffer units 200 arranged in a mirror image. The buffer unit 200 is provided with a plurality of obliquely arranged support rod bodies 220, and adjacent two support rod bodies 220 are rotatably connected through a torsion spring for self-adaptively adjusting its own length to adapt to the landing on terrains of different heights.

[0037] The buffer unit 200 includes 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; a plurality of support rod bodies 220 are provided, and they are all arranged at the bottom of the L-shaped plate 210. The support rod body 220 located above is rotatably connected to the horizontal section of the L-shaped plate 210, and adjacent two support rod bodies 220 are rotatably connected through a torsion spring; the foot support plate 230 is fixed to the bottom of the support rod body 220 located below for providing stable ground support.

[0039] A plurality of the support rod bodies 220 are combined to form a multi-segment elastic telescopic structure. When the UAV fuselage 100 touches the ground, each group of support rod bodies 220 self-adaptively adjusts its own length and expands and contracts according to the pressure at the contact point under the action of the self-landing gravity of the UAV fuselage 100 to keep the fuselage balanced.

[0040] The top of the foot support plate 230 is made of an iron structure, and an electromagnet is arranged at the bottom of the buffer chassis 120. In the initial state, when the electromagnet is energized, the foot support plate 230 drives the support rod body 220 to contract under the magnetic attraction effect. During landing, the electromagnet is powered off, and the foot support plate 230 descends by itself under the action of gravity and drives the support rod body 220 to naturally expand.

[0041] The electromagnet is used to control the contraction and relaxation of the foot support plate 230 and the support rod body 220, which is a prior art and will not be elaborated here.

[0042] When the embodiment of the present application is actually running, the steps are as follows: First, when the drone fuselage 100 flies to the predetermined landing area, the electromagnet is powered off, and the foot support plate 230 descends by itself under the action of gravity and drives the support rod body 220 to naturally relax. At this time, the buffer unit 200 is in a natural relaxation state; then, when the drone descends and starts to contact the ground, under the action of the slow descent of the drone and gravity, multiple groups of support rod bodies 220 respectively adapt to the landing terrain and perform independent compression until the drone fuselage 100 remains horizontal and lands smoothly on the ground.

[0043] The technical solutions in the above embodiments of the present application have at least the following technical effects or advantages:

[0044] By setting the buffer units 200 evenly distributed in the present application, different ground contact points can be independently responded to, and "local fine-tuning" can be achieved through the adaptive adjustment of the support rod body 220 to avoid the tilting of the fuselage; the support rod body 220 is rotationally connected by a torsion spring to form a segmented elastic structure, so that the buffer unit 200 can gradually absorb impact energy under the action of gravity and avoid single-point overload; and the L-shaped plate 210 elastically fixes the support rod body 220, and the anti-slip design of the foot support plate 230 can disperse the impact force, and the two cooperate to buffer and form a "two-stage buffer system" to improve the buffer effect; each group of buffer units 200 can independently adjust the contact surface angle and support height according to the ground undulation, adjust the height by itself, keep the fuselage horizontal, adapt to the terrain change, reduce the tilting risk, and at the same time the structure is simpler and more reliable, which can improve the balance landing ability of the drone on the uneven terrain.

[0045] Embodiment 2: When the support rod body 220 contacts a slope or a protrusion, since the main rod 221 may have different deformations when being pressed at different angles during the bending and folding process of the support rod bodies 220 at different positions, the main rod 221 with single-axial telescoping is prone to lateral deformation instability, resulting in the phenomenon of twisting or collapse of the main rod 221 when tilted. In view of the above technical problems, the present application proposes the following technical solutions, specifically:

[0046] As Figure 3 shown in Figure 4 the support rod body 220 includes a main rod 221 and a sub-support rod 240;

[0047] The main rod 221 is a thick-diameter structure, which is responsible for telescopic movement and provides basic support stiffness; the sub-support rod 240 is a thin-diameter structure, which is evenly wound around the outer wall of the main rod 221 and provides lateral support for the main rod 221.

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

[0049] In this application, through the cooperation of the main rod 221 and the secondary support rods 240, and by uniformly winding the secondary support rods 240 along the length direction of the main rod 221, an additional lateral support force is provided for the main rod 221. This structural complementarity makes the entire support rod system more stable when facing lateral pressure and not prone to twisting or collapse; the presence of the secondary support rods 240 effectively increases the shear resistance of the support rod system. Therefore, during the landing process of the drone, especially when contacting a slope or a protrusion, the support rod system may be subjected to lateral forces from different directions. Through its uniformly wound design, the secondary support rods 240 can effectively disperse and resist these lateral forces, enhance the flexural rigidity of the main rod 221, and thus maintain the overall stability of the support rod body 220, enabling the drone to contact the ground more smoothly during the landing process, not only improving the safety of the drone but also extending its service life.

[0050] Embodiment 3: When the secondary support rods 240 are wound around the outside of the main rod 221 in a fixed helix, only the lateral force in a single direction is optimized. When multi-directional impacts occur simultaneously, the radial expansion of the secondary support rods 240 cannot evenly cover all directions, resulting in insufficient local flexural rigidity. In response to the above technical problems, this application proposes the following technical solutions, specifically:

[0051] As Figures 3 to 7 shown, three groups of secondary support rods 240 are provided, which are divided into the first secondary support rod 241, the second secondary support rod 242, and the third secondary support rod 243, and are wound around the outside of the main rod 221 at helix angles of 45°, 0°, and 90° respectively, for providing lateral support force for the main rod 221.

[0052] The first secondary support rod 241 is wound around the outside of the main rod 221 at a 45° helix angle; a plurality of the second secondary 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 of the third secondary support rods 243 are arranged up and down, for combining and connecting the first secondary support rod 241 and the second secondary support rod 242 into a surrounding diamond grid structure and strengthening the outer edge of the main rod 221; the three groups of secondary support rods 240 form diamond grid nodes through laser welding at the intersection points.

[0053] The diamond grid nodes formed by laser welding have excellent fatigue resistance, further enhancing the overall structure of the support rod system. During long-term use, these nodes can maintain a stable connection state. These nodes not only fix the positions of the secondary support rods 240 but also disperse the stress through the grid form, making the support rod system more stable when facing complex stress states and not prone to loosening or breaking.

[0054] In this application, three sets of auxiliary struts 240 are arranged and wound around the outer side of the main strut 221 at different helix angles, forming a three-dimensional helical reinforcement structure. This structure not only increases the radial stiffness of the strut system but also improves its anti-torsion ability. Therefore, when contacting slopes or protrusions, the helical auxiliary struts 240 and the diamond grid nodes can provide additional lateral support force for the main strut 221. This lateral support force effectively prevents the distortion or collapse of the main strut 221, thus maintaining the balance and stability of the drone. In particular, the circumferential annular winding of the 90° set of auxiliary struts three 243 provides additional circumferential constraint for the strut system, effectively preventing the lateral deformation of the main strut 221.

[0055] At the same time, the helically wound auxiliary struts 240 and the diamond grid nodes enable the stress to be more evenly distributed throughout the strut system, effectively reducing the phenomenon of stress concentration and improving the durability and reliability of the strut system. Moreover, during the landing process of the drone, the strut system is subjected to impacts and vibrations from the ground, and the helical auxiliary struts 240 and the diamond grid nodes can absorb and relieve these impacts and vibrations, thereby protecting the drone fuselage 100 from damage and enabling the drone to maintain the balance of the fuselage more stably and reliably when landing on complex terrains.

[0056] Embodiment 4: In order to further improve the smoothness of the drone landing and flexibly adapt to impacts from different directions, in response to the above technical problems, this application proposes the following technical solution, specifically:

[0057] As Figures 4 to 8 shown, the buffer unit 200 further includes an adjustment mechanism 250 for controlling the tension force of the diamond grid structure formed by the combination of the auxiliary struts 240. The adjustment mechanism 250 includes a cross slot 251, an electric slider 252, and a convex block 253;

[0058] A plurality of groups of the cross slots 251 are provided and are all opened on the outer surface of the main strut 221; a plurality of groups of the convex blocks 253 are provided and are in one-to-one correspondence with the cross slots 251, and are respectively slidably connected in the corresponding cross slots 251 through the electric sliders 252, and are used for pulling the diamond-shaped mesh structure in a certain direction by moving, so as to adjust its tension force.

[0059] Each group of the cross slots 251 includes two cross slots 251 arranged up and down, and the left and right adjacent groups of cross slots 251 are arranged up and down in a staggered manner, so as to adapt to impacts from different positions and directions, and further adjust the anti-impact ability of different positions of the whole strut body 220.

[0060] A plurality of cameras 130 are fixedly installed in the middle of the bottom surface of the buffer chassis 120 for detecting impacts from different directions; the electric slider 252 is controlled to move through 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 external control system issues an instruction to control the movement of the electric slider 252 at the corresponding position.

[0061] The external control system is used to control the movement of the electric sliders 252 at different positions, and then pull different positions of the mesh structure of the auxiliary support rods 240 to change its tension force. Preferably, it is a programmable logic controller, which is prior art and will not be elaborated here. Through the coordinated use of the adjustment mechanism 250 and the camera 130, the intelligent control of the buffer device is realized. The camera 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 slider 252 based on this information, thereby realizing the automatic adjustment and optimization of the buffer device.

[0062] During the actual operation of this embodiment: during the falling process of the UAV fuselage 100, the ground terrain is monitored in real time by the camera 130. When it is detected that it is about to contact uneven or inclined ground or an impact is about to come from a certain direction, the camera 130 transmits the terrain information to the external control system; then, the external control system controls the electric slider 252 in the corresponding direction to slide in the cross groove 251 according to the terrain information and the external impact force, drives the convex block 253 to move, and then pulls the diamond-shaped mesh structure formed by the auxiliary support rods 240 to change the tension force of the diamond-shaped mesh structure to make it adapt to impacts in a specific direction; finally, after a smooth landing, the convex block 253 returns to its original position and the diamond-shaped mesh structure returns to its original state.

[0063] When the UAV is impacted, the main rod 221 may be deformed or local stress concentration may occur. The adjustment mechanism 250 can effectively disperse and relieve stress by changing the tension force of the mesh structure formed by the auxiliary support rods 240, avoiding damage to the main rod 221 due to excessive stress. This not only helps to reduce the damage to the UAV caused by impacts, but also improves the overall durability of the device.

[0064] In the present application, by sliding the electric slider 252 within the cross slot 251, the position of the bump 253 can be precisely controlled, thereby driving the rhombic network structure formed by the secondary support rods 240 to be pulled in a specific direction. This adjustment mechanism enables the device to quickly adapt to impacts from different directions, improving the dynamic response ability and stability of the device. By using the electric slider 252 in cooperation with the camera 130, when the camera 130 detects an impact from a certain direction, the external control system can control the electric slider 252 to drive the bump 253 to move up or down or left or right, thereby driving the rhombic network structure formed by multiple secondary support rods 240 to be pulled in a certain direction (i.e., changing its tension), causing the network structure formed by the outer secondary support rods 240 to be pulled and deformed in a certain direction, thereby being able to adapt to impacts from different directions and improving the local stress on the outside of the main rod 221, so as to flexibly adjust the rigidity or tensile stress at 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 are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, various changes and modifications can be made to the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. Buffer device for drone landing, comprising a drone fuselage (100) and a fan blade (110), wherein a buffer chassis (120) is fixedly installed at the bottom of the drone fuselage (100), and is characterized in that, A buffer unit (200) for the landing of the drone is fixed below the buffer chassis (120); Multiple groups of the buffer units (200) are provided and arranged evenly in a matrix. Each group includes two mirror - arranged buffer units (200). The buffer unit (200) is provided with a plurality of obliquely arranged support rods (220), and adjacent two support rods (220) are rotationally connected by torsion springs, and are used to adaptively adjust their own lengths to adapt to landings on terrains of different heights.

2. The buffer device for the landing of the unmanned aerial vehicle according to claim 1, characterized in that, The buffer unit (200) includes an L - shaped plate (210), a support rod (220) and a foot support plate (230); The L - shaped plate (210) is fixed below the buffer chassis (120) to provide a fixed basis for the support rod (220); A plurality of support rods (220) are provided, and they are all arranged at the bottom of the L - shaped plate (210). The support rod (220) located above is rotationally connected to the horizontal section of the L - shaped plate (210), and adjacent two support rods (220) are rotationally connected by torsion springs; The foot support plate (230) is fixed at the bottom of the support rod (220) located below and is used to provide stable ground support.

3. The buffer device for the drone landing according to claim 2, characterized in that, The multiple support rods (220) are combined to form a multi - section elastic telescopic structure. When the drone fuselage (100) touches the ground, each group of support rods (220) adaptively adjusts its own length under the action of the landing gravity of the drone fuselage (100) and expands and contracts according to the pressure at the contact point to keep the fuselage balanced.

4. The buffer device for drone landing according to claim 3, wherein, The support rod (220) includes a main rod (221) and a sub - support rod (240); The main rod (221) is of a thick - diameter structure and is used to be responsible for telescopic movement and provide basic support stiffness; The sub - support rod (240) is of a thin - diameter structure and is evenly wound around the outer wall of the main rod (221) and is used to provide lateral support for the main rod (221).

5. The buffer device for the landing of the drone according to claim 4, characterized in that There are three groups of the sub - support rods (240), which are divided into a first sub - support rod (241), a second sub - support rod (242) and a third sub - support rod (243), and are wound around the outside of the main rod (221) at helix angles of 45°, 0° and 90° respectively, and are used to provide lateral support force for the main rod (221).

6. The buffer device for the landing of the unmanned aerial vehicle according to claim 5, wherein, The first sub - support rod (241) is wound around the outside of the main rod (221) at a 45° helix angle; A plurality of the second sub - support rods (242) are provided, and they all extend parallel to the axis of the main rod (221) and are fixed on the outside of the main rod (221); There are two third sub - support rods (243) arranged up and down, and are used to combine and connect the first sub - support rod (241) and the second sub - support rod (242) into a surrounding diamond - shaped grid structure and reinforce the outer edge of the main rod (221); The three groups of sub - support rods (240) form diamond - shaped grid nodes by laser welding at the intersection points.

7. The buffer device for the drone landing according to claim 6, characterized in that, The buffer unit (200) further includes an adjusting mechanism (250) for controlling the tension of the diamond - shaped grid structure formed by the combination of the sub - support rods (240). The adjusting mechanism (250) includes a cross - slot (251), an electric slider (252) and a convex block (253); A plurality of sets of the cross grooves (251) are provided and are all formed on the outer surface of the main rod (221); a plurality of sets of the bumps (253) are provided, corresponding to the cross grooves (251) one by one, and are respectively slidably connected in the corresponding cross grooves (251) through electric sliders (252) for pulling the diamond mesh structure in a certain direction by moving, so as to adjust its tension force.

8. The buffer device for the landing of the drone according to claim 7, wherein, Each set of the cross grooves (251) includes two cross grooves (251) arranged up and down, and two sets of adjacent cross grooves (251) on the left and right are arranged staggeredly up and down for adapting to impacts from different positions and directions, so as to adjust the impact resistance of different positions of the whole strut body (220).

9. The buffer device for the landing of the drone according to claim 8, wherein, A plurality of cameras (130) are fixed in the middle of the bottom surface of the buffer chassis (120) for detecting impacts from different directions; the electric slider (252) is controlled to move through 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 external control system issues an instruction to control the movement of the electric slider (252) at the corresponding position.

10. The buffer device for the landing of the drone according to claim 8, characterized in that, The top of the foot support plate (230) is made of an iron structure, and an electromagnet is arranged at the bottom of the buffer chassis (120). In the initial state, when the electromagnet is powered on, the foot support plate (230) drives the strut body (220) to contract under the magnetic attraction effect. When landing, the electromagnet is powered off, and the foot support plate (230) descends by itself under the action of gravity and drives the strut body (220) to naturally expand.

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