Unmanned aerial vehicle undercarriage with flight anti-collision pressure relief structure

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and particularly discloses an unmanned aerial vehicle undercarriage with a flight anti-collision pressure relief structure, which comprises a pressure relief structure, a heightening assembly and an anti-collision structure, the heightening assembly is movably arranged on the pressure relief structure, the anti-collision structure is detachably arranged on the heightening assembly, multiple buffering mechanisms are provided, and when an unmanned aerial vehicle lands, the pressure relief structure conducts pressure relief buffering through a first spring under the action of descending gravity; in this way, impact force generated during landing can be effectively dispersed and absorbed, and the influence of the impact force on the unmanned aerial vehicle is further reduced through vertical buffering of the heightening assembly; when the arc-shaped protection claws in the anti-collision structure turn over towards the outer side, auxiliary supporting can be achieved, stable landing is facilitated, and when the protection claws turn over towards the inner side relatively, the unmanned aerial vehicle can be surrounded for shielding protection.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a landing gear of an unmanned aerial vehicle provided with a flight anti-collision pressure relief structure. Background Art

[0002] Unmanned aircraft, referred to as "drones", are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are fully or intermittently operated autonomously by onboard computers; existing drones are large in size and weight, and therefore require landing gear for takeoff and landing;

[0003] When the drone takes off, the landing gear provides stable support for the drone, ensuring that the drone can leave the ground smoothly; during landing, the landing gear cushions the impact force between the drone and the ground, preventing damage to the bottom structure and internal equipment of the drone;

[0004] Although the existing landing gear can support the UAV fuselage, it is mostly a fixed structure, which is not enough to better reduce the cushioning and unloading of the gravity pressure during landing. In addition, the landing gear is only arranged at the bottom of the fuselage, which cannot effectively protect the UAV after taking off. It is too simple. Therefore, a UAV landing gear with a flight anti-collision pressure relief structure is designed. Summary of the invention

[0005] The object of the present invention is to provide a UAV landing gear provided with a flight anti-collision pressure relief structure to solve the problems raised in the above-mentioned background technology.

[0006] In order to achieve the above-mentioned solution to the problem, the present invention provides the following technical solution: a UAV landing gear provided with a flight anti-collision pressure relief structure, comprising a pressure relief structure, a height-enhancing component and an anti-collision structure; the height-enhancing component is movably arranged on the pressure relief structure, and the anti-collision structure is detachably arranged on the height-enhancing component.

[0007] Preferably, the pressure relief structure includes a pressure relief frame, two pairs of legs, two pairs of frames, two pairs of first sliding bars, two pairs of first baffles, two pairs of first springs and two pairs of connecting rods; the pressure relief frame is a rectangular frame, and telescopic holes are symmetrically arranged near the four corners, one end of the two pairs of legs are movably arranged in the middle of the side wall of the pressure relief frame, and the legs are inclined in four directions respectively, the two pairs of frames are concave structures, the two pairs of frames are equidistantly arranged in the middle of the inner side wall of the pressure relief frame, and the frames correspond to the legs respectively, one end of the two pairs of the first sliding bars are movably passed through the middle of the side wall of the frame and are respectively screwed into the inner side wall of the pressure relief frame, the two pairs of the first baffles are respectively movably embedded in the frame, and the first baffles are respectively movably mounted on the first sliding bars, the two pairs of the first springs are respectively movably mounted on the first sliding bars and the first springs are located between the first baffle and the pressure relief frame, one end of the two pairs of connecting rods are respectively movably connected to the middle of the lower wall of the legs, and the other end of the connecting rods are respectively tilted and movably connected to the middle of the lower wall of the first baffle.

[0008] Preferably, the height-increasing assembly includes a pad, four pairs of sleeves, four pairs of second sliding rods and four pairs of second springs; the pad is a rectangular structure, and the pad is movably arranged above the pressure relief frame. The four pairs of sleeves are symmetrically welded to the lower wall of the pad and correspond to the telescopic holes respectively. One ends of the four pairs of second sliding rods are movably passed through the telescopic holes of the pressure relief frame, and the other ends of the second sliding rods are inserted in the sleeves, and the other ends of the second sliding rods are movably screwed into the lower wall of the pad, and the four pairs of the second springs are movably sleeved on the second sliding rods, and one ends of the second springs are movably inserted in the sleeves, and the other ends of the second springs are attached to the upper wall of the pressure relief frame.

[0009] Preferably, the anti-collision structure includes a mounting ring, four pairs of rollers, four pairs of protective claws, a plurality of first connecting rods, a plurality of second connecting rods, a center table, a motor, a pulley, a transmission belt and two pairs of clamping ring assemblies; the mounting ring is a circular ring structure, and the four pairs of rollers are equidistantly and movably mounted on the mounting ring, and the four pairs of rollers rotate around the mounting ring and cannot move left and right, and a belt groove is provided on the outer wall at one end of one of the rollers, and the four pairs of protective claws are arc-shaped, and one end of the four pairs of protective claws is fixedly arranged on the side wall of the roller, and the inner wall of the protective claws faces upward, one end of the plurality of first connecting rods is movably connected to the upper wall at both ends of the roller, and the plurality of second connecting rods are movably connected to the upper wall at both ends of the roller, and the plurality of second The two ends of the two connecting rods are movably connected between the other end of the first connecting rod, and the second connecting rod is located in the mounting ring, one end of the center platform is fixedly mounted on the mounting ring and one end of the center platform is located near one of the rollers, the other end of the center platform is circular, and the other end of the center platform is located in the center of the mounting ring, the motor is fixedly arranged on the lower wall of one end of the center platform, and a transfer line is arranged on the motor, the pulley is fixedly mounted on the driving end of the motor, and the pulley corresponds to the belt groove of one of the rollers, the two ends of the transmission belt are movably mounted on the pulley and the belt groove of one of the rollers, and the two pairs of the retaining ring assemblies are removably arranged on the upper wall of the center platform.

[0010] Preferably, the center platform is detachably mounted on the pad by bolts.

[0011] Preferably, the clamping ring assembly is composed of a pair of relatively fitting semicircular claws that are relatively movably connected, and the other ends are relatively fixed by bolts, and the lower wall of one of the claws in the clamping ring assembly is provided with a docking plate connected to the center platform.

[0012] Preferably, the first connecting rod and the second connecting rod are both located outside the pad and cannot contact the pad.

[0013] Preferably, the other end of the protective claw is located above the other end of the supporting leg, and the other end of the protective claw and the other end of the supporting leg can contact the ground at the same time.

[0014] The invention proposes a drone landing gear provided with a flight anti-collision pressure relief structure, which has the following beneficial effects: in this scheme, the pressure relief structure is used as the bottom structure of the landing gear, and when subjected to the descending gravity, the pressure relief structure can relieve pressure and buffer through the first spring, and at the same time, with the help of the height-increasing component, the vertical descending pressure buffering is realized for effective protection, and the drone can be supported to a certain height to facilitate take-off; the arc-shaped protective claws in the anti-collision structure can be flipped and controlled, and when the protective claws are flipped outward, they can assist in supporting and stabilizing the landing, and when the protective claws are relatively flipped inward, the drone can be surrounded for shielding and protection, so as to prevent the fuselage or propeller from being damaged by collision during flight;

[0015] In summary, the present invention has multiple buffering mechanisms:

[0016] When the UAV is landing, it is affected by the downward gravity, and the pressure relief structure performs pressure relief and buffering through the first spring; this method can effectively disperse and absorb the impact force during landing.

[0017] Vertical cushioning of the height-enhancing component: The height-enhancing component cushions the pressure of vertical descent, which adds another layer of protection during the landing process and further reduces the impact of impact on the drone.

[0018] Adapt to different landing conditions: This multiple buffering mechanism enables the drone to perform well in different landing scenarios, whether on relatively flat ground or slightly undulating field environments, it can effectively buffer the impact force during landing and reduce the risk of damage to the drone.

[0019] The support height is convenient for takeoff: The landing gear can support the drone to a certain height. During takeoff, sufficient support height can ensure that the propeller of the drone has a sufficient safe distance from the ground to prevent the propeller from touching the ground during rotation.

[0020] Stable landing: When the arc-shaped protective claws in the anti-collision structure flip outward, they can provide auxiliary support, which helps to stabilize the landing. During the landing process, the drone needs to maintain balance and stability, and the auxiliary support of the protective claws has several additional support points.

[0021] Encirclement protection: When the protective claws flip inward, they can surround the drone for shielding and protection to prevent damage to the fuselage or propellers during flight. During the flight of the drone, it may encounter various obstacles, such as tree branches, buildings, etc. The encirclement protection of the protective claws can to a certain extent prevent the drone from directly colliding with these obstacles. For example, when flying through the woods for aerial photography, the protective claws can prevent branches from scratching the drone's fuselage or breaking the propellers, thereby protecting the drone's key components and extending the drone's service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the assembly structure of the present invention;

[0023] Figure 2 It is a schematic diagram of the split structure of the pressure relief structure of the present invention;

[0024] Figure 3 It is a schematic diagram showing the structure of the height-increasing component of the present invention;

[0025] Figure 4 The schematic diagram of the anti-collision structure of the present invention is shown;

[0026] Figure 5 It is a schematic diagram of the partial enlarged structure of A of the present invention;

[0027] Figure 6 It is a schematic diagram of the partial enlarged structure of B of the present invention;

[0028] Figure 7 It is a schematic diagram of the partially enlarged structure of location C of the present invention.

[0029] In the figure: 1. pressure relief structure, 11. pressure relief frame, 12. support foot, 13. frame, 14. first slide bar, 15. first baffle, 16. first spring, 17. connecting rod, 2. height increase component, 21. pad, 22. sleeve, 23. second slide bar, 24. second spring, 3. anti-collision structure, 31. mounting ring, 32. four pairs of rollers, 33. protective claw, 34. first connecting rod, 35. second connecting rod, 36. center table, 37. motor, 38. pulley, 39. transmission belt, 40. retaining ring assembly, 5. belt groove. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] See also Figure 1-Figure 7 The present invention provides a technical solution: a UAV landing gear with a flight anti-collision pressure relief structure, comprising a pressure relief structure 1, a heightening component 2 and an anti-collision structure 3; the heightening component 2 is movably arranged on the pressure relief structure 1, and the anti-collision structure 3 is detachably arranged on the heightening component 2; the pressure relief structure 1 is used for supporting the fuselage and the first buffer pressure relief during landing, the heightening component 2 is used to increase the height of the supported fuselage and is also used for the second buffer pressure relief during landing, and the anti-collision structure 3 is used for auxiliary support of the fuselage during landing and protection and anti-collision after take-off.

[0032] As a further solution of the present invention, the pressure relief structure 1 includes a pressure relief frame 11, two pairs of legs 12, two pairs of frames 13, two pairs of first slide bars 14, two pairs of first baffles 15, two pairs of first springs 16 and two pairs of connecting rods 17; the pressure relief frame 11 is a rectangular frame, and telescopic holes are symmetrically arranged near the four corners, one end of the two pairs of legs 12 are movably arranged in the middle of the side wall of the pressure relief frame 11, and the legs 12 are inclined in four directions respectively, the two pairs of frames 13 are concave structures, the two pairs of frames 13 are equidistantly arranged in the middle of the inner wall of the pressure relief frame 11, and the frames 13 correspond to the legs 12 respectively, one end of the two pairs of the first slide bars 14 are movably passed through the middle of the side wall of the frame 13 and are respectively screwed to the pressure relief In the inner wall of the frame 11, two pairs of the first baffles 15 are respectively movably embedded in the frame 13, and the first baffles 15 are respectively movably mounted on the first slide bar 14, and the two pairs of the first springs 16 are respectively movably mounted on the first slide bar 14 and the first spring 16 is located between the first baffle 15 and the pressure relief frame 11, and one end of the two pairs of the connecting rods 17 are respectively movably connected to the middle part of the lower wall of the support leg 12, and the other end of the connecting rod 17 is respectively tilted and movably connected to the middle part of the lower wall of the first baffle 15; the pressure relief frame 11 is forced to drop during landing, causing the support leg 12 to be forced to flip outward, and at the same time, the flipping of the support leg 12 will pull the first baffle 15 and compress the first spring 16 through the connecting rod 17, thereby achieving pressure buffering with the help of the first spring 16.

[0033] As a further solution of the present invention, the height-increasing component 2 includes a pad 21, four pairs of sleeves 22, four pairs of second slide bars 23 and four pairs of second springs 24; the pad 21 is a rectangular structure, the pad 21 is movably arranged above the pressure relief frame 11, the four pairs of sleeves 22 are symmetrically welded to the lower wall of the pad 21 and respectively correspond to the telescopic holes, one end of the four pairs of second slide bars 23 are movably passed through the telescopic holes of the pressure relief frame 11, and the other end of the second slide bar 23 is inserted into the sleeve 22, and the other end of the second slide bar 23 is movably screwed to the bottom of the pad 21 The four pairs of the second springs 24 are movably mounted on the second slide bar 23, and one end of the second spring 24 is movably inserted in the sleeve 22, and the other end of the second spring 24 is attached to the upper wall of the pressure relief frame 11; the pad 21 is pressed down by the gravity when the fuselage lands, so as to compress the second spring 24 mounted on the second slide bar 23 to achieve buffering pressure relief. At the same time, since a sleeve 22 is provided under the pad 21, the second spring 24 is compressed to the maximum until the sleeve 22 contacts the pressure relief frame 11, so as to ensure that the pad 21 is located above the pressure relief frame 11 and has a certain height to support the fuselage.

[0034] As a further solution of the present invention, the anti-collision structure 3 includes a mounting ring 31, four pairs of rollers 32, four pairs of protective claws 33, a plurality of first connecting rods 34, a plurality of second connecting rods 35, a center platform 36, a motor 37, a pulley 38, a transmission belt 39 and two pairs of clamping ring assemblies 40; the mounting ring 31 is a circular ring structure, and the four pairs of rollers 32 are respectively and equidistantly mounted on the mounting ring 31, and the four pairs of rollers 32 rotate around the mounting ring 31 and cannot move left and right, and a belt groove 5 is opened on the outer wall of one end of one of the rollers 32, and the four pairs of protective claws 33 are all arc-shaped, and one end of the four pairs of protective claws 33 is respectively fixedly set at The first connecting rods 34 are movably connected to the upper walls of the two ends of the roller 32, and the second connecting rods 35 are movably connected between the other ends of the first connecting rods 34, and the second connecting rods 35 are located in the mounting ring 31. One end of the center platform 36 is fixedly sleeved on the mounting ring 31 and one end of the center platform 36 is located near one of the rollers 32. The other end of the center platform 36 is circular and the other end of the center platform 36 is located in the center of the mounting ring 31. The motor 37 is fixedly arranged on the lower wall of one end of the center platform 36, and the motor 37 is provided with a switching The belt pulley 38 is fixedly mounted on the driving end of the motor 37, and the belt pulley 38 corresponds to the belt groove 5 of one of the rollers 32. The two ends of the transmission belt 39 are movably mounted on the belt pulley 38 and the belt groove 5 of one of the rollers 32. The two pairs of the clamping ring assemblies 40 are detachably mounted on the upper wall of the center platform 36. The device is fixed to the existing landing gear under the fuselage through the clamping ring assembly 40, or fixed to the belly of the fuselage through the center platform 36. When in use, the motor 37 is connected to the fuselage and energized. The motor 37 is controlled to rotate by the controller of the drone, and the belt pulley 38 is driven to rotate by the motor 37. The transmission belt 39 drives one of the rollers 32 to rotate on the mounting ring 31, and realizes a series linkage through the connection between the second connecting rod 35 and the first connecting rod 34 between the two rollers 32, driving the rollers 32 to rotate on the mounting ring 31 at the same time to drive the protective claws 33 to flip. When landing, the protective claws 33 flip outward and are located on the outside of the pressure relief structure 1. When the support legs 12 are forced to flip to a certain extent, as the pressure relief frame 11 is lowered and the pad 21 is lowered to a certain height, the other end of the protective claws 33 is prompted to contact the ground for auxiliary support to ensure stable landing. After takeoff, the protective claws 33 are relatively flipped and are located on the outside of the fuselage for shielding and collision prevention.

[0035] As a further solution of the present invention, the center platform 36 is detachably mounted on the pad 21 by bolts for design and installation requirements, so that the anti-collision structure 3 can be directly used on the drone for landing support and take-off protection.

[0036] As a further solution of the present invention, the snap ring assembly 40 is composed of a pair of relatively fitting semicircular claws that are relatively movably connected, and the other ends are relatively fixed by bolts, and the lower wall of one of the claws in the snap ring assembly 40 is provided with a docking plate connected to the center platform 36, which is used for the existing technical structure and is convenient for fixing on the existing landing gear rod body.

[0037] As a further solution of the present invention, the first connecting rod 34 and the second connecting rod 35 are both located outside the pad 21 and cannot contact the pad 21, which is used to design linkage requirements.

[0038] As a further solution of the present invention, the other end of the protective claw 33 is located above the other end of the support leg 12, and the other end of the protective claw 33 and the other end of the support leg 12 can contact the ground at the same time, which is designed to assist landing and increase stability.

[0039] The detailed connection means are well-known in the art. The following mainly introduces the working principle and process. The specific work is as follows.

[0040] First, the clamping ring assembly 40 in the anti-collision structure 3 is connected and installed with the existing landing gear rod at the bottom of the drone, or the clamping ring assembly 40 is removed according to needs and connected to the drone body through the center platform 36, and the adapter cable of the motor 37 is connected to the drone, and controlled by the controller;

[0041] When in use, the support legs 12 in the pressure relief structure 1 are in contact with the ground for support, and the height of the supporting fuselage is increased by the heightening component 2, which is conducive to the generation of airflow for the drone to take off;

[0042] When the UAV takes off, the control motor 37 drives the pulley 38 to rotate, prompting the transmission belt 39 to drive one of the rollers 32 to rotate on the mounting ring 31, and the second connecting rod 35 is connected to the first connecting rod 34 at both ends of the roller 32 to form a series connection, thereby driving the roller 32 to synchronously rotate a corresponding angle on the mounting ring 31, so that the protective claw 33 can be relatively flipped and located outside the propeller of the UAV body to form a shielding protection to avoid damage to the propeller and the fuselage due to collision during flight;

[0043] When the drone lands, the motor 37 drives the protective claw 33 to flip in the opposite direction and be located outside the pressure relief structure 1; at the same time, as the drone lands, the support foot 12 is the first to contact the ground and be subjected to force, and the gravity of the drone will be applied to the pad 21 in the height-increasing component 2. The pad 21 is subjected to force and drops, which will compress the second spring 24 limited by the second slide bar 23, and the pressure relief buffer is performed by the second spring 24. At the same time, the descending height of the pad 21 is limited, and the maximum is when the sleeve 22 contacts the pressure relief frame 11, and the sleeve 22 keeps the pad 21 at a certain height to support the fuselage;

[0044] Then the gravity of the fuselage will be applied to the pressure relief frame 11. As the pressure relief frame 11 is forced to drop, the support leg 12 will be forced to flip to a certain angle. At the same time, the flipping of the support leg 12 will pull the first baffle 15 through the linkage rod 17. Then, the first baffle 15 is forced to move on the first slide bar 14 through the shielding of the frame 13 to compress the first spring 16. The first spring 16 is used to buffer and relieve pressure on the support leg 12 and the pressure relief frame 11 to prevent impact damage caused by the drop of gravity.

[0045] When landing, if the protective claw 33 is flipped over and located outside the pressure relief structure 1, the pressure relief frame 11 will be lowered and the pad 21 will be lowered to a certain height as the support leg 12 is flipped over and buffered, and then the other end of the protective claw 33 will contact the ground as the height is lowered, and the auxiliary support leg 12 will provide stable support;

[0046] When landing, if the protective claws 33 are not turned over and located outside the pressure relief structure 1, they are always located outside the fuselage for shielding and protection, which can ensure that the fuselage is effectively protected if it falls over during landing;

[0047] The above-mentioned anti-collision structure 3 can be directly mounted on the fuselage through the central platform 36, and the fuselage can be supported by the reverse flipping of the protection claws 33, and can be relatively flipped for protection after take-off.

[0048] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A UAV landing gear with a flight anti-collision pressure relief structure, characterized in that: It comprises a pressure relief structure (1), a height-enhancing component (2) and an anti-collision structure (3); the height-enhancing component (2) is movably mounted on the pressure relief structure (1), and the anti-collision structure (3) is detachably mounted on the height-enhancing component (2).

2. The UAV landing gear with a flight anti-collision pressure relief structure according to claim 1, characterized in that: The pressure relief structure (1) comprises a pressure relief frame (11), two pairs of supporting legs (12), two pairs of frames (13), two pairs of first sliding rods (14), two pairs of first blocking plates (15), two pairs of first springs (16) and two pairs of connecting rods (17); The pressure relief frame (11) is a rectangular frame, and telescopic holes are symmetrically arranged near the four corners. One end of the two pairs of legs (12) is movably arranged in the middle of the side wall of the pressure relief frame (11), and the legs (12) are inclined in four directions. The two pairs of frames (13) are both concave structures. The two pairs of frames (13) are equidistantly arranged in the middle of the inner side wall of the pressure relief frame (11), and the frames (13) correspond to the legs (12) respectively. One end of the two pairs of the first sliding rods (14) is movably passed through the middle of the side wall of the frame (13) and is respectively screwed to the pressure relief frame (11). In the inner wall of the pressure frame (11), two pairs of the first baffles (15) are respectively movably embedded in the frame (13), and the first baffles (15) are respectively movably mounted on the first slide bar (14), two pairs of the first springs (16) are respectively movably mounted on the first slide bar (14), and the first springs (16) are located between the first baffles (15) and the pressure relief frame (11), one end of the two pairs of the connecting rods (17) are respectively movably connected to the middle part of the lower wall of the support foot (12), and the other end of the connecting rod (17) is respectively tilted and movably connected to the middle part of the lower wall of the first baffle (15).

3. The UAV landing gear with a flight anti-collision pressure relief structure according to claim 2, characterized in that: The height-increasing assembly (2) comprises a backing plate (21), four pairs of sleeves (22), four pairs of second sliding rods (23) and four pairs of second springs (24); The pad (21) is a rectangular structure. The pad (21) is movably arranged above the pressure relief frame (11). The four pairs of sleeves (22) are symmetrically welded to the lower wall of the pad (21) and correspond to the telescopic holes respectively. One end of the four pairs of second slide bars (23) are movably passed through the telescopic holes of the pressure relief frame (11), and the other end of the second slide bar (23) is inserted into the sleeve (22). The other end of the second slide bar (23) is movably screwed into the lower wall of the pad (21). The four pairs of second springs (24) are movably sleeved on the second slide bars (23), and one end of the second spring (24) is movably inserted into the sleeve (22), and the other end of the second spring (24) is attached to the upper wall of the pressure relief frame (11).

4. The UAV landing gear with a flight anti-collision pressure relief structure according to claim 3, characterized in that: The anti-collision structure (3) comprises a mounting ring (31), four pairs of rotating rollers (32), four pairs of protective claws (33), a plurality of first connecting rods (34), a plurality of second connecting rods (35), a central platform (36), a motor (37), a pulley (38), a transmission belt (39) and two pairs of snap ring assemblies (40); The mounting ring (31) is a circular ring structure. The four pairs of rollers (32) are equidistantly mounted on the mounting ring (31). The four pairs of rollers (32) rotate around the mounting ring (31) and cannot move left or right. A belt groove (5) is provided on the outer wall of one end of one of the rollers (32). The four pairs of protective claws (33) are all arc-shaped. One end of the four pairs of protective claws (33) is fixedly arranged on the side wall of the roller (32), and the inner wall of the protective claws (33) faces upward. One end of a plurality of first connecting rods (34) is movably connected to the upper wall of the two ends of the roller (32). Two ends of a plurality of second connecting rods (35) are movably connected between the other ends of the first connecting rods (34), and the second connecting rods (35) are located in the mounting ring (31). The center platform (36) one end is fixedly mounted on the mounting ring (31) and one end of the center platform (36) is located near one of the rollers (32), the other end of the center platform (36) is circular, and the other end of the center platform (36) is located in the center of the mounting ring (31), the motor (37) is fixedly arranged on the lower wall of one end of the center platform (36), and the motor (37) is provided with a switching line, the pulley (38) is fixedly mounted on the driving end of the motor (37), and the pulley (38) corresponds to the belt groove (5) of one of the rollers (32), the two ends of the transmission belt (39) are movably mounted on the pulley (38) and the belt groove (5) of one of the rollers (32), and the two pairs of the clamping ring assemblies (40) are respectively detachably arranged on the upper wall of the center platform (36).

5. The UAV landing gear with a flight anti-collision pressure relief structure according to claim 4, characterized in that: The center platform (36) is detachably mounted on the backing plate (21) by means of bolts.

6. The unmanned aerial vehicle landing gear with a flight anti-collision pressure relief structure according to claim 5, characterized in that: The clamping ring assembly (40) is composed of a pair of relatively matching semicircular clamping claws that are relatively movably connected, and the other ends are relatively fixed by bolts, and a docking plate connected to the center platform (36) is provided on the lower wall of one of the clamping claws in the clamping ring assembly (40).

7. The UAV landing gear with a flight anti-collision pressure relief structure according to claim 6, characterized in that: The first connecting rod (34) and the second connecting rod (35) are both located outside the pad (21) and cannot contact the pad (21).

8. The UAV landing gear with a flight anti-collision pressure relief structure according to claim 7, characterized in that: The other ends of the protective claws (33) are respectively located above the other ends of the supporting legs (12), and the other ends of the protective claws (33) and the other ends of the supporting legs (12) can contact the ground at the same time.

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