A drone flight collision avoidance device

Abstract

A drone flight collision avoidance device, belonging to the field of aircraft technology, addresses the problem that existing drone landing gears are mostly fixed rigid support structures, only suitable for flat, hard ground, and prone to tipping over or sinking on inclined, soft, or gravel surfaces. The invention includes an aircraft shell, with a first camera and a second camera fixedly installed on the side wall of the shell. A lifting structure is fixedly installed in the inner cavity at the bottom of the shell, and a sponge anti-slip plate is fixedly installed at the bottom of the lifting structure. This invention uses the second camera to identify ground conditions, and in conjunction with a retractable landing structure and balancing components, relies on a balance sensor to calibrate the levelness of the balancing platform in real time. This allows for the creation of a horizontal landing reference surface on uneven ground, significantly overcoming landing site limitations and effectively avoiding drone tipping and fuselage damage caused by tilted landings. It significantly improves landing adaptability and safety in complex outdoor environments.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to a collision avoidance device for unmanned aerial vehicles (UAVs). Background Technology

[0002] With the rapid development of low-altitude inspection, agricultural and forestry operations, logistics and distribution and other fields, the application scenarios of drones are becoming more and more intensive, and the flight environment is becoming more and more complex. They are prone to encountering obstacles such as buildings, tree branches, birds and other aircraft, resulting in frequent collision accidents. These accidents not only cause damage to the fuselage and rotors, but also pose safety hazards such as crashes that injure people and interrupt operations.

[0003] Currently, conventional drone landing gear is generally a fixed, rigid structure, lacking active leveling and attitude correction functions. This limits its applicability, allowing it to be used only on flat, hard surfaces. In special situations, such as field operations, facing complex terrains like slopes and uneven surfaces, the landing gear experiences uneven stress and unstable support, easily causing the drone to lose balance and tip over, significantly reducing the safety and environmental adaptability of drones for field landings.

[0004] To address the above issues, a drone flight collision avoidance device is proposed. Summary of the Invention

[0005] The purpose of this invention is to provide a drone flight collision avoidance device. By using this device, the problem that existing drone landing gear is mostly a fixed rigid support structure, which is only suitable for flat and hard ground, and is prone to tipping over and sinking on inclined, soft, and gravel roads is solved.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a drone flight collision avoidance device, comprising an aircraft shell, a first camera fixedly installed on the side wall of the aircraft shell, a second camera fixedly installed on the side wall of the aircraft shell, a lifting structure fixedly installed in the inner cavity at the bottom of the aircraft shell, a sponge anti-slip plate fixedly installed at the bottom of the lifting structure, a landing structure fixedly installed at the top of the sponge anti-slip plate, a balancing structure fixedly installed at the top of the sponge anti-slip plate, a balancing sensor fixedly installed at the bottom of the balancing structure, a small inflatable tank fixedly installed in the inner cavity of the landing structure, a folding airbag fixedly installed at one end of the small inflatable tank, and multiple anti-slip structures fixedly installed at the bottom of the sponge anti-slip plate.

[0007] Furthermore, the aircraft shell includes a fuselage fixedly installed on the outer wall of the No. 1 camera, wings fixedly installed on the outer walls of the four sides of the fuselage, frames fixedly installed on the left and right sides of the bottom of the fuselage, and a conical chassis fixedly installed in the inner cavity of the bottom of the fuselage.

[0008] Furthermore, the landing structure includes a landing frame inserted into the fuselage cavity, a limit frame fixedly installed at the bottom of the landing frame, a protective plate rotatably connected to the inner cavity of the outer wall of the landing frame, a magnetic sheet fixedly installed on the inner wall of the outer wall of the landing frame, and the side wall of the protective plate magnetically attracted to the outer wall of the magnetic sheet, a sliding groove is provided at the bottom of the landing frame, and a sliding hole is provided on the inner wall of the landing frame.

[0009] Furthermore, the lifting structure includes a No. 1 dual-axis motor fixedly installed in the inner cavity of the machine body, lifting rollers fixedly installed on the output ends of the No. 1 dual-axis motor on the left and right sides, lifting ropes fixedly connected to the outer wall of the lifting rollers, and the bottom of the lifting ropes fixedly installed to the top of the sponge anti-slip plate.

[0010] Furthermore, the balancing structure includes a balancing chassis fixedly installed on the top of the sponge anti-slip plate. Two dual-axis motors are fixedly installed on all four sides of the top of the balancing chassis. A balancing plate is fixedly installed on the output end of the two dual-axis motors on the left side. A semi-enclosed circular sleeve is fixedly installed on one end of the balancing plate. A support rod is rotatably connected to the inner cavity of the semi-enclosed circular sleeve. A second semi-enclosed circular sleeve is rotatably connected to one end of the top of the support rod.

[0011] Furthermore, a balancing ring is fixedly installed on the top of the second semi-enclosed circular sleeve, and the outer wall of the balancing ring passes through the slide tube. A third semi-enclosed circular sleeve is fixedly installed on the top of the balance chassis. An electric telescopic rod is rotatably connected to the inner cavity of the third semi-enclosed circular sleeve. A fourth semi-enclosed circular sleeve is rotatably connected to the top of the electric telescopic rod. The top of the fourth semi-enclosed circular sleeve is fixedly installed to the bottom of the balance sensor. A balancing platform is fixedly installed on the top of the balance sensor. A slide rod is fixedly installed on the bottom frame of the balancing platform. The outer wall of the slide rod is slidably connected to the inner cavity of the slide tube.

[0012] Furthermore, an eccentric wheel is fixedly installed on the output end of the second dual-axis motor on the right side. A pulling rod is rotatably connected to the outer wall of the eccentric wheel, and a connecting frame is rotatably connected to one end of the pulling rod.

[0013] Furthermore, the anti-slip structure includes a limiting tube fixedly installed on the top of the sponge anti-slip plate, a stop block fixedly installed on the inner wall of the limiting tube, and a positioning cone slidably connected to the inner cavity of the limiting tube.

[0014] Furthermore, a lower pressure frame is fixedly installed on the top of the positioning cone, the bottom of the lower pressure frame is fixedly installed on the top of the connecting frame, and a limit plate is slidably connected to the inner cavity of the positioning cone.

[0015] Furthermore, a fixed slide rod is fixedly installed at the bottom of the limiting plate, and the outer wall of the fixed slide rod is slidably connected to the inner cavity wall of the positioning cone. Fixed rods are rotatably connected to both sides of the bottom of the fixed slide rod, and a cone block is rotatably connected to one end of the fixed rod.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. By identifying ground conditions through the second camera, and in conjunction with the demountable landing structure and balancing components, the levelness of the balancing platform can be calibrated in real time by the balancing sensor. This allows for the construction of a horizontal landing reference surface on uneven ground, significantly overcoming landing site limitations and effectively avoiding problems such as drone tipping and fuselage damage caused by tilted landings. This significantly improves the drone's adaptability and safety in complex outdoor environments.

[0017] 2. A small inflatable tank and a folding airbag are built into the landing structure. When landing, the airbag is inflated simultaneously to expand outward and form a ring-shaped limiting barrier. This can not only block the lateral displacement and tilting tendency of the UAV during landing, but also provide physical isolation and buffer against surrounding debris and obstacles, preventing the fuselage rotor and shell from directly colliding with foreign objects.

[0018] 3. The linkage balance drive mechanism triggers the anti-slip structure, causing the positioning cone of the anti-slip structure to extend and penetrate the ground. When the positioning cone enters the soil, it uses the limiting effect of the stop block on the limiting plate to pull the fixed sliding rod and the fixed rod in the opposite direction, driving the cone block to extend laterally and clamp into the soil, thereby effectively resisting external pulling force, strengthening the pull-out resistance, and the anchoring reliability is far superior to the conventional straight cone positioning method. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the landing frame structure of the present invention; Figure 3 This is a bottom-view schematic diagram of the fuselage of the present invention; Figure 4 This is a top view of the landing frame of the present invention; Figure 5 This is a schematic cross-sectional view of the folding airbag of the present invention; Figure 6 This is a schematic cross-sectional view of the groove of the present invention; Figure 7 This is a schematic cross-sectional view of the limiting tube of the present invention; Figure 8 This is a schematic diagram of the balanced chassis structure of the present invention; Figure 9 This is a schematic diagram of the balancing platform structure of the present invention.

[0020] In the diagram: 1. Aircraft outer shell; 11. Fuselage; 12. Wing; 13. Frame; 14. Conical chassis; 2. Camera 1; 3. Camera 2; 4. Landing structure; 41. Landing frame; 42. Limiting frame; 43. Protective plate; 44. Magnetic sheet; 45. Slide groove; 46. Sliding hole; 5. Sponge anti-slip plate; 6. Lifting structure; 61. First dual-axis motor; 62. Lifting roller; 63. Lifting rope; 7. Balance sensor; 8. Balance structure; 81. Balance chassis; 82. Second dual-axis motor; 821. Eccentric wheel; 822. Pull rod; 8 23. Connecting frame; 83. Balancing plate; 831. No. 1 semi-enclosed round sleeve; 832. Support rod; 833. No. 2 semi-enclosed round sleeve; 84. Balancing ring; 841. Sliding tube; 85. No. 3 semi-enclosed round sleeve; 851. Electric telescopic rod; 852. Balancing platform; 853. Sliding rod; 854. No. 4 semi-enclosed round sleeve; 9. Small air tank; 10. Folding airbag; 20. Anti-slip structure; 201. Limiting tube; 202. Stop block; 203. Positioning cone; 204. Limiting plate; 205. Fixed sliding rod; 206. Fixed rod; 207. Cone block; 208. Lower pressure frame. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] To address the technical problem that existing drone landing gears are mostly fixed, rigid support structures, only suitable for flat, hard ground, and prone to tipping over or sinking on sloping, soft, or gravel surfaces, such as... Figures 1-9 As shown, the following preferred technical solution is provided: A drone flight anti-collision device includes an aircraft shell 1, a first camera 2 fixedly installed on the side wall of the aircraft shell 1, and the first camera 2 is used to transmit images back in real time during the drone's flight, a second camera 3 fixedly installed on the side wall of the aircraft shell 1, a lifting structure 6 fixedly installed in the inner cavity at the bottom of the aircraft shell 1, a sponge anti-slip plate 5 fixedly installed at the bottom of the lifting structure 6, a landing structure 4 fixedly installed on the top of the sponge anti-slip plate 5, a balancing structure 8 fixedly installed on the top of the sponge anti-slip plate 5, a balancing sensor 7 fixedly installed at the bottom of the balancing structure 8, a small inflatable tank 9 fixedly installed in the inner cavity of the landing structure 4, a folding airbag 10 fixedly installed at one end of the small inflatable tank 9, and multiple anti-slip structures 20 fixedly installed at the bottom of the sponge anti-slip plate 5.

[0023] Specifically, when the drone is preparing to land, it is first lowered to a preset height that facilitates landing. The ground conditions are detected by the second camera 3. If the ground is tilted or other conditions are not conducive to landing, the self-locking function of the lifting structure 6 can be released by the backend. Then, the lifting structure 6 drives the landing structure 4 and the sponge anti-slip plate 5 to descend until the sponge anti-slip plate 5 contacts the ground. After the sponge anti-slip plate 5 lands, the backend activates the balancing structure 8, drives the balancing structure 8 to support the landing platform, and calibrates the levelness of the landing platform of the balancing structure 8 according to the balance sensor 7 to keep the platform level for the drone to land smoothly.

[0024] Furthermore, when the aircraft shell 1 lands on the support platform, the second camera 3 collects the horizontal reference of the support platform, solidifies the zero position and deviation threshold, and compares and calibrates the visual recognition accuracy. If the aircraft becomes unstable or tilts on the support platform and the deviation exceeds the preset threshold, it is determined that a tipping has occurred. At this time, the airbag protection is activated. By opening the valve of the small inflatable tank 9, air is inflated into the inner cavity of the folded airbag 10, causing the folded airbag 10 to expand and extend along the land structure 4, thereby forming a limiting barrier protection on the outside of the drone to prevent the drone from tilting or deviating during landing and directly hitting the ground. If the aircraft lands smoothly on the support platform, the airbag is not needed, thus providing an emergency measure for drone landing.

[0025] If camera 3 detects that the ground is gravel or mud, it first activates the anti-slip structure 20 to enhance the anti-slip performance of the bottom of the sponge anti-slip plate 5. Then, it uses the balancing structure 8 to perform level calibration, keeping the landing platform level. Finally, it controls the drone to complete the landing maneuver. By using the balancing structure 8 to drive and press the anti-slip structure 20, the anti-slip structure 20 can extend from the bottom of the sponge anti-slip plate 5 and penetrate into the ground to achieve anchoring and fixation, thereby improving the anti-slip and anti-sinking performance of the bottom of the sponge anti-slip plate 5 and ensuring a stable landing for the drone. However, if camera 3 detects that the ground is cement, tile, or other hard surfaces, the balancing structure 8 will not drive the anti-slip structure 20 to prevent mechanical damage.

[0026] Once the drone takes off again and climbs to a preset altitude, which is limited to a low range to prevent the drone from swaying due to wind force when it takes off too high, the lifting structure 6 is activated to perform the recovery action, lifting the landing structure 4 and the foam anti-slip plate 5 from the ground until the bottom of the landing structure 4 is inserted into the inner cavity of the aircraft shell 1, thus completing the storage and recovery of the entire structure.

[0027] like Figures 2-7As shown, the aircraft shell 1 includes a fuselage 11 fixedly mounted on the outer wall of the first camera 2. Wings 12 are fixedly mounted on the outer walls of the four sides of the fuselage 11. Frames 13 are fixedly mounted on the left and right sides of the bottom of the fuselage 11. A conical chassis 14 is fixedly mounted in the inner cavity of the bottom of the fuselage 11, and the bottom of the conical chassis 14 is conical to facilitate insertion into the recess of the landing platform for auxiliary positioning during subsequent drone landing. The landing structure 4 includes a landing frame 41 inserted into the inner cavity of the fuselage 11. A limit frame 42 is fixedly mounted on the bottom of the landing frame 41. A protective plate 43 is rotatably connected to the inner cavity of the outer wall of the landing frame 41. A magnetic sheet 44 is fixedly mounted on the inner wall of the outer wall of the landing frame 41, and the side wall of the protective plate 43 is magnetically attached to the outer wall of the magnetic sheet 44. When the small inflatable canister 9 inflates the folding airbag 10, the expansion of the folding airbag 10 compresses the protective plate 43. The sidewalls allow the protective plate 43 to escape the magnetic force of the magnetic sheet 44. The bottom of the landing frame 41 has a sliding groove 45, and the inner wall of the landing frame 41 has a sliding hole 46. The lifting structure 6 includes a first dual-axis motor 61 fixedly installed in the inner cavity of the body 11. Lifting rollers 62 are fixedly installed on the output ends of the first dual-axis motor 61 on the left and right sides. When the first dual-axis motor 61 is started, it can drive the lifting rollers 62 on the left and right sides to rotate synchronously. The outer wall of the lifting roller 62 is fixedly connected to a lifting rope 63. The bottom of the lifting rope 63 is fixedly installed to the top of the sponge anti-slip plate 5. By starting the first dual-axis motor 61, the output end of the first dual-axis motor 61 drives the lifting roller 62 to rotate, thereby releasing the lifting rope 63, suspending the landing frame 41 and the sponge anti-slip plate 5 to descend until the sponge anti-slip plate 5 contacts the ground.

[0028] like Figure 6 , Figure 7 and Figure 9 As shown, the balancing structure 8 includes a balancing chassis 81 fixedly installed on the top of the sponge anti-slip plate 5. Two dual-axis motors 82 are fixedly installed on all four sides of the top of the balancing chassis 81. The two output ends of the dual-axis motors 82 can be controlled to rotate independently, which facilitates subsequent adjustment of the landing platform and the anti-slip structure 20. A balancing plate 83 is fixedly installed on the left output end of the dual-axis motors 82. A semi-enclosed circular sleeve 831 is fixedly installed on one end of the balancing plate 83. A support rod 832 is rotatably connected to the inner cavity of the semi-enclosed circular sleeve 831. A second semi-enclosed circular sleeve 833 is rotatably connected to the top end of the support rod 832. The two ends of the support rod 832 are spherical and are limited by the inner cavity of the semi-enclosed circular sleeve 831, which is equivalent to the ball joint structure of the prior art, so that the angle of the connection between the support rod 832 and the semi-enclosed circular sleeve 831 can be adjusted within a certain range.

[0029] A balancing ring 84 is fixedly installed on the top of the second semi-enclosed circular sleeve 833. The outer wall of the balancing ring 84 passes through the sliding tube 841. A third semi-enclosed circular sleeve 85 is fixedly installed on the top of the balance base 81. An electric telescopic rod 851 is rotatably connected to the inner cavity of the third semi-enclosed circular sleeve 85. A fourth semi-enclosed circular sleeve 854 is rotatably connected to the top of the electric telescopic rod 851. The top of the fourth semi-enclosed circular sleeve 854 is fixedly installed to the bottom of the balance sensor 7. A balancing platform 852 is fixedly installed on the top of the balance sensor 7. A conical groove is provided in the middle of the balancing platform 852. When the UAV lands, the conical base 14 with a conical structure at its bottom can be inserted into the conical groove to achieve automatic positioning, which facilitates the UAV to land accurately on the balancing platform 852 and return. When retrieving the drone landing structure 4, the drone can be guided, stored, and retrieved by relying on the alignment and cooperation between the conical chassis 14 and the balancing platform 852. A sliding rod 853 is fixedly installed on the bottom frame of the balancing platform 852. The outer wall of the sliding rod 853 is slidably connected to the inner cavity of the sliding tube 841. The upper and lower ends of the electric telescopic rod 851 are also set as spheres. By cooperating with the third semi-enclosed circular sleeve 85 and the fourth semi-enclosed circular sleeve 854, the effect of the ball joint structure is achieved, which facilitates the adjustment according to the angle position of the balancing platform 852. An eccentric wheel 821 is fixedly installed on the output end of the second dual-axis motor 82. The outer wall of the eccentric wheel 821 is rotatably connected to the pull rod 822. One end of the pull rod 822 is rotatably connected to the connecting frame 823.

[0030] Specifically, when the second camera 3 detects that the landing environment is a sloping, hard surface, it controls the first dual-axis motor 61 to drive the sponge anti-slip plate 5 downwards. Since the ground material does not require the activation of the anti-slip structure 20, the balancing structure 8 directly corrects the level of the landing platform. The level status of the balancing platform 852 is monitored in real time by the balance sensor 7. If the balancing platform 852 is detected to be tilted, the second dual-axis motor 82, located on the side of the balancing platform 852 that is tilted too low, is activated. The output of the second dual-axis motor 82... The end drives the balancing plate 83 and the first semi-enclosed circular sleeve 831 to rotate, which in turn pushes the support rod 832, causing the support rod 832 to lift the second semi-enclosed circular sleeve 833 and the balancing ring 84, thereby completing the horizontal calibration of the balancing ring 84. After the balancing ring 84 is leveled, the electric telescopic rod 851 is automatically started according to the preset program, driving the balancing platform 852 to rise, so that the slide rod 853 slides in the inner cavity of the slide tube 841 and achieves limit locking. Finally, the raised balancing platform 852 serves as a landing platform to receive the UAV.

[0031] To address the technical problem of limited anti-slip capability at the bottom of existing conventional landing gear, leading to slippage and subsidence on soft mud, sand, and gravel surfaces, resulting in landing instability, such as... Figures 5-9As shown, the following preferred technical solution is provided: The anti-slip structure 20 includes a limiting tube 201 fixedly installed on the top of the sponge anti-slip plate 5. A stop block 202 is fixedly installed on the inner wall of the limiting tube 201. A positioning cone 203 is slidably connected to the inner cavity of the limiting tube 201. A lower pressure frame 208 is fixedly installed on the top of the positioning cone 203. The bottom of the lower pressure frame 208 is fixedly installed on the top of the connecting frame 823. A limiting plate 204 is slidably connected to the inner cavity of the positioning cone 203. A fixed sliding rod 205 is fixedly installed on the bottom of the limiting plate 204. The outer wall of the fixed sliding rod 205 is slidably connected to the inner wall of the positioning cone 203. Fixed rods 206 are rotatably connected to both sides of the bottom of the fixed sliding rod 205. A cone block 207 is rotatably connected to one end of the fixed rod 206.

[0032] Specifically, after the sponge anti-slip plate 5 lands, if the second camera 3 detects that the ground is not hard and is soft terrain, to avoid insufficient anti-slip performance of the sponge anti-slip plate 5 affecting the drone's landing, the second dual-axis motor 82 can be started first. Its right output end drives the eccentric wheel 821 to rotate rapidly half a turn. The side wall of the eccentric wheel 821 pulls one end of the pull rod 822 downwards, and then the connecting frame 823 synchronously drives the lower pressure frame 208 to descend rapidly. Thus, the lower pressure frame 208 pushes the positioning cone 203 in the inner cavity of the limiting tube 201 downwards and inserts it into the ground. During the process of positioning cone 203 entering the soil, limiting plate 204 is blocked and limited by stop block 202, and cannot move down with positioning cone 203. As a result, limiting plate 204 pulls fixed slide bar 205, and fixed slide bar 205 pulls fixed rod 206, so fixed rod 206 can squeeze and push cone block 207 out of the inner cavity of positioning cone 203, so that cone block 207 is exposed and stuck in the soil, enhancing the anti-pull-out effect of positioning cone 203. Then, the leveling state of balancing platform 852 is detected by balance sensor 7 and leveling is performed at the same time. Finally, the drone is controlled to land.

[0033] When the positioning cone 203 is retracted, the second dual-axis motor 82 rotates half a turn in the opposite direction, driving the lower pressure frame 208 to move upward. At the same time, the limiting plate 204 is pressed against the inner wall of the limiting tube 201. The cone block 207 is retracted into the inner cavity of the positioning cone 203 by displacement, thus completing the overall retraction and reset.

[0034] Once the anti-slip structure 20 has retracted and reset, the No. 1 dual-axis motor 61 is restarted. Relying on the reverse rotation of the No. 1 dual-axis motor 61, the sponge anti-slip plate 5 is pulled upward until the top of the landing frame 41 is inserted into the inner cavity of the body 11. Then, the self-locking function of the No. 1 dual-axis motor 61 is used to lock the lifting roller 62, thereby completing the overall recovery of the landing structure 4.

[0035] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

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

Claims

1. A drone flight collision avoidance device, comprising an aircraft shell (1), characterized in that: A first camera (2) is fixedly installed on the side wall of the aircraft shell (1), a second camera (3) is fixedly installed on the side wall of the aircraft shell (1), a lifting structure (6) is fixedly installed in the inner cavity at the bottom of the aircraft shell (1), a sponge anti-slip plate (5) is fixedly installed at the bottom of the lifting structure (6), a landing structure (4) is fixedly installed on the top of the sponge anti-slip plate (5), a balancing structure (8) is fixedly installed on the top of the sponge anti-slip plate (5), a balancing sensor (7) is fixedly installed at the bottom of the balancing structure (8), a small air tank (9) is fixedly installed in the inner cavity of the landing structure (4), a folding airbag (10) is fixedly installed at one end of the small air tank (9), and multiple anti-slip structures (20) are fixedly installed at the bottom of the sponge anti-slip plate (5).

2. The anti-collision device for unmanned aerial vehicles according to claim 1, characterized in that: The aircraft shell (1) includes a fuselage (11) fixedly installed on the outer wall of the No. 1 camera (2), wings (12) fixedly installed on the outer walls of the four sides of the fuselage (11), frames (13) fixedly installed on the left and right sides of the bottom of the fuselage (11), and a conical chassis (14) fixedly installed in the inner cavity of the bottom of the fuselage (11).

3. The anti-collision device for unmanned aerial vehicles according to claim 2, characterized in that: The landing structure (4) includes a landing frame (41) inserted into the inner cavity of the fuselage (11). A limit frame (42) is fixedly installed at the bottom of the landing frame (41). A protective plate (43) is rotatably connected to the inner cavity of the outer wall of the landing frame (41). A magnetic sheet (44) is fixedly installed on the inner wall of the outer wall of the landing frame (41), and the side wall of the protective plate (43) is magnetically attracted to the outer wall of the magnetic sheet (44). A sliding groove (45) is opened at the bottom of the landing frame (41), and a sliding hole (46) is opened in the inner wall of the landing frame (41).

4. The anti-collision device for unmanned aerial vehicles according to claim 2, characterized in that: The lifting structure (6) includes a No. 1 dual-axis motor (61) fixedly installed in the inner cavity of the body (11). Lifting rollers (62) are fixedly installed on the output ends of the No. 1 dual-axis motor (61) on the left and right sides. Lifting ropes (63) are fixedly connected to the outer wall of the lifting rollers (62). The bottom of the lifting ropes (63) is fixedly installed on the top of the sponge anti-slip plate (5).

5. The anti-collision device for unmanned aerial vehicles according to claim 1, characterized in that: The balancing structure (8) includes a balancing chassis (81) fixedly installed on the top of the sponge anti-slip plate (5). Two dual-axis motors (82) are fixedly installed on the four sides of the top of the balancing chassis (81). A balancing plate (83) is fixedly installed on the output end of the two dual-axis motors (82) on the left side. A first semi-enclosed round sleeve (831) is fixedly installed on one end of the balancing plate (83). A support rod (832) is rotatably connected to the inner cavity of the first semi-enclosed round sleeve (831). A second semi-enclosed round sleeve (833) is rotatably connected to one end of the top of the support rod (832).

6. The anti-collision device for unmanned aerial vehicles according to claim 5, characterized in that: The top of the second semi-enclosed round sleeve (833) is fixedly installed with a balancing ring (84), the outer wall of the balancing ring (84) passes through the slide tube (841), the top of the balance chassis (81) is fixedly installed with a third semi-enclosed round sleeve (85), the inner cavity of the third semi-enclosed round sleeve (85) is rotatably connected with an electric telescopic rod (851), the top of the electric telescopic rod (851) is rotatably connected with a fourth semi-enclosed round sleeve (854), the top of the fourth semi-enclosed round sleeve (854) is fixedly installed with the bottom of the balance sensor (7), the top of the balance sensor (7) is fixedly installed with a balancing platform (852), the bottom edge of the balancing platform (852) is fixedly installed with a slide rod (853), the outer wall of the slide rod (853) is slidably connected with the inner cavity of the slide tube (841).

7. The anti-collision device for unmanned aerial vehicles according to claim 5, characterized in that: An eccentric wheel (821) is fixedly installed on the output end of the second dual-axis motor (82) on the right side. A pull rod (822) is rotatably connected to the outer wall of the eccentric wheel (821), and a connecting frame (823) is rotatably connected to one end of the pull rod (822).

8. The anti-collision device for unmanned aerial vehicles according to claim 7, characterized in that: The anti-slip structure (20) includes a limiting tube (201) fixedly installed on the top of the sponge anti-slip plate (5), a stop block (202) fixedly installed on the inner wall of the limiting tube (201), and a positioning cone (203) slidably connected to the inner cavity of the limiting tube (201).

9. A drone flight collision avoidance device according to claim 8, characterized in that: The top of the positioning cone (203) is fixedly installed with a lower pressure frame (208), the bottom of the lower pressure frame (208) is fixedly installed with the top of the connecting frame (823), and the inner cavity of the positioning cone (203) is slidably connected with a limit plate (204).

10. A drone flight collision avoidance device according to claim 9, characterized in that: The bottom of the limiting plate (204) is fixedly installed with a fixed slide rod (205), and the outer wall of the fixed slide rod (205) is slidably connected to the inner wall of the positioning cone (203). Both sides of the bottom of the fixed slide rod (205) are rotatably connected with fixed rods (206), and one end of the fixed rod (206) is rotatably connected with a cone block (207).

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