A landing gear for unmanned aerial vehicles equipped with a flight collision avoidance and pressure relief structure

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically disclosing a UAV landing gear equipped with a flight anti-collision and pressure relief structure, including a pressure relief structure, a height-increasing component, and an anti-collision structure. The height-increasing component is movably mounted on the pressure relief structure, and the anti-collision structure is detachably mounted on the height-increasing component. This invention has multiple buffering mechanisms. When the UAV lands, it is subjected to the force of gravity during descent, and the pressure relief structure provides pressure relief and buffering through a first spring. This method can effectively disperse and absorb the impact force during landing, and the vertical buffering of the height-increasing component further reduces the impact force on the UAV. When the arc-shaped protective claw in the anti-collision structure flips outward, it can provide auxiliary support and help stabilize the landing. When the protective claw flips inward, it can surround and protect the UAV.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV landing gear equipped with a flight anti-collision and pressure relief structure. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and onboard program control devices, or operated autonomously by an onboard computer, either completely or intermittently. Existing UAVs are relatively large and heavy, thus requiring landing gear for takeoff and landing.

[0003] When a drone takes off, the landing gear provides stable support, 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 drone's bottom structure and internal equipment.

[0004] While existing landing gear can support the fuselage of a drone, it is mostly a fixed structure, which is insufficient to reduce the impact of gravity during landing and unload the pressure caused by descent. Furthermore, the landing gear is only located at the bottom of the fuselage and cannot effectively protect the drone after takeoff, making it too simplistic. Therefore, a drone landing gear with a flight anti-collision and pressure relief structure is designed. Summary of the Invention

[0005] The purpose of this invention is to provide a drone landing gear with a flight anti-collision and pressure relief structure to solve the problems mentioned in the background art.

[0006] To address the aforementioned problems, the present invention provides the following technical solution: a drone landing gear equipped with a flight anti-collision and pressure relief structure, comprising a pressure relief structure, a height-increasing component, and an anti-collision structure; the height-increasing component is movably mounted on the pressure relief structure, and the anti-collision structure is detachably mounted on the height-increasing 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 rods, two pairs of first baffles, two pairs of first springs, and two pairs of connecting rods. The pressure relief frame is a rectangular frame with telescopic holes symmetrically arranged near the four corners. One end of each pair of legs is movably mounted in the middle of the side wall of the pressure relief frame, and the legs are inclined in four directions. Both 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. One end of each pair of first sliding rods movably passes through the middle of the side wall of the frame and is screwed into the inner side wall of the pressure relief frame. The two pairs of first baffles are movably embedded in the frame, and the first baffles are movably mounted on the first sliding rods. The two pairs of first springs are movably mounted on the first sliding rods, and the first springs are located between the first baffles and the pressure relief frame. One end of each pair of connecting rods is movably connected to the middle of the lower wall of the legs, and the other end of each connecting rod is inclined and movably connected to the middle of the lower wall of the first baffle.

[0008] Preferably, the heightening assembly includes a pad, four pairs of sleeves, four pairs of second slide rods, and four pairs of second springs; the pad is a rectangular structure and is movably mounted 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 end of each of the four pairs of second slide rods movably passes through the telescopic hole of the pressure relief frame, and the other end of the second slide rod is inserted into the sleeve; the other end of the second slide rod is movably screwed into the lower wall of the pad; the four pairs of second springs are movably mounted on the second slide rods, and one end of the second spring is movably inserted into the sleeve; the other end of the second spring is attached to the upper wall of the pressure relief frame.

[0009] Preferably, the anti-collision structure includes a mounting ring, four pairs of rotating rollers, four pairs of protective claws, several first connecting rods, several second connecting rods, a center platform, a motor, pulleys, a transmission belt, and two pairs of retaining ring assemblies. The mounting ring is a circular ring structure. The four pairs of rotating rollers are equidistantly mounted on the mounting ring. All four pairs of rotating rollers rotate around the mounting ring and cannot move left or right. One end of one of the rotating rollers has a groove on its outer side wall. All four pairs of protective claws are arc-shaped. One end of each of the four pairs of protective claws is fixedly mounted on the side wall of the rotating roller, with the inner side wall of the protective claw facing upward. One end of each of the first connecting rods is movably connected to the upper walls of both ends of the rotating roller. The two ends of the second connecting rod are movably connected between the other ends of the first connecting rod, and the second connecting rod is located inside the mounting ring. One end of the central platform is fixedly fitted onto the mounting ring and is located near one of the rotating rollers. The other end of the central platform is circular and is located in the center of the mounting ring. The motor is fixedly mounted on the lower wall of one end of the central platform and has an adapter cable. The pulley is fixedly fitted onto the motor drive end and corresponds to the groove of one of the rotating rollers. The two ends of the transmission belt are movably fitted onto the pulley and the groove of one of the rotating rollers, respectively. The two pairs of retaining ring assemblies are detachably mounted on the upper wall of the central platform.

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

[0011] Preferably, the retaining ring assembly consists of a pair of relatively mating semi-circular retaining claws that are movably connected to each other, and the other end is fixed relative to each other by bolts, and a docking plate connected to the central platform is provided on the lower wall of one of the retaining claws in the retaining ring assembly.

[0012] Preferably, both the first link and the second link are 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 support leg, and the other end of the protective claw and the other end of the support leg can simultaneously contact the ground.

[0014] The present invention proposes a drone landing gear with a flight anti-collision and pressure relief structure, which has the following advantages: This solution uses the pressure relief structure as the bottom structure of the landing gear. When subjected to the force of gravity during descent, the pressure relief structure can provide pressure relief and buffering through the first spring. At the same time, the height-increasing component can effectively protect against the pressure of vertical descent and support the drone at a certain height to facilitate takeoff. The arc-shaped protective claws in the anti-collision structure can be flipped and controlled. When the protective claws are flipped outward, they can provide additional support to help stabilize the landing. When the protective claws are flipped inward, they can surround and shield the drone to prevent damage to the fuselage or propeller during flight.

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

[0016] When the drone lands, it is subjected to the force of gravity during descent, and the pressure relief structure uses the first spring to provide pressure relief and buffer; this method can effectively disperse and absorb the impact force during landing.

[0017] Vertical buffering of the height-increasing assembly: The height-increasing assembly buffers and protects against the pressure of vertical descent, adding another layer of protection to the landing process and further reducing the impact of the impact on the drone.

[0018] Adaptable to different landing conditions: This multi-buffering mechanism enables the drone to perform well in different landing scenarios. Whether on relatively flat ground or in slightly undulating outdoor environments, it can effectively buffer the impact of landing and reduce the risk of damage to the drone.

[0019] Support height facilitates takeoff: The landing gear can support the drone at a certain height. During takeoff, sufficient support height can ensure that the drone's propellers have a safe distance from the ground, preventing the propellers from touching the ground during rotation.

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

[0021] Encircling protection: When the protective claws flip inwards, they can surround and shield the drone, preventing damage to the fuselage or propeller during flight. During drone flight, various obstacles may be encountered, such as tree branches and buildings. This encircling protection of the protective claws can, to some extent, prevent the drone from directly colliding with these obstacles. For example, when conducting aerial photography through forests, the protective claws can prevent tree branches from scratching the drone's fuselage or breaking the propeller, thereby protecting the drone's critical components and extending its service life. Attached Figure Description

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

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

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

[0025] Figure 4 This is a schematic diagram illustrating the anti-collision structure of the present invention;

[0026] Figure 5 This is a partially enlarged structural diagram of point A in the present invention;

[0027] Figure 6 This is a partially enlarged structural diagram of point B in the present invention;

[0028] Figure 7 This is a partially enlarged structural diagram of point C in the present invention.

[0029] In the diagram: 1. Pressure relief structure, 11. Pressure relief frame, 12. Support leg, 13. Frame, 14. First slide rod, 15. First baffle, 16. First spring, 17. Linkage rod, 2. Heightening assembly, 21. Pad, 22. Sleeve, 23. Second slide rod, 24. Second spring, 3. Anti-collision structure, 31. Mounting ring, 32. Four pairs of rotating rollers, 33. Protective claw, 34. First connecting rod, 35. Second connecting rod, 36. Center platform, 37. Motor, 38. Pulley, 39. Transmission belt, 40. Snap ring assembly, 5. Groove. Detailed Implementation

[0030] 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.

[0031] Please see Figures 1-7 The present invention provides a technical solution: a landing gear for a drone equipped with a flight anti-collision and pressure relief structure, comprising a pressure relief structure 1, a height-increasing component 2, and an anti-collision structure 3; the height-increasing component 2 is movably mounted on the pressure relief structure 1, and the anti-collision structure 3 is detachably mounted on the height-increasing component 2; the pressure relief structure 1 is used to support the fuselage and provide first-stage pressure relief during landing, the height-increasing component 2 increases the height of the supported fuselage and also provides second-stage pressure relief during landing, and the anti-collision structure 3 is used for auxiliary support during landing and for protection against collisions after takeoff.

[0032] As a further embodiment of the present invention, the pressure relief structure 1 includes a pressure relief frame 11, two pairs of support legs 12, two pairs of frames 13, two pairs of first sliding rods 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 each of the two pairs of support legs 12 is movably mounted in the middle of the side wall of the pressure relief frame 11, and the support legs 12 are inclined in four directions. Both pairs of frames 13 are concave structures, and 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 support legs 12. One end of each of the two pairs of first sliding rods 14 movably passes through the middle of the side wall of the frame 13 and is screwed to the pressure relief frame. Inside the inner wall of the frame 11, two pairs of the first baffles 15 are movably embedded in the frame 13, and the first baffles 15 are movably mounted on the first slide rod 14. Two pairs of the first springs 16 are movably mounted on the first slide rod 14, and the first springs 16 are located between the first baffles 15 and the pressure relief frame 11. One end of each pair of connecting rods 17 is movably connected to the middle of the lower wall of the support leg 12, and the other end of each connecting rod 17 is movably connected to the middle of the lower wall of the first baffle 15. When the pressure relief frame 11 is lowered by force during descent, the support leg 12 is forced to flip outward. At the same time, the flipping of the support leg 12 will pull the first baffles 15 and compress the first springs 16 through the connecting rods 17, thereby achieving pressure buffering by means of the first springs 16.

[0033] As a further embodiment of the present invention, the height-increasing component 2 includes a pad 21, four pairs of sleeves 22, four pairs of second sliding rods 23, and four pairs of second springs 24. The pad 21 has a rectangular structure and is movably mounted 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. One end of each of the four pairs of second sliding rods 23 movably passes through the telescopic holes of the pressure relief frame 11, and the other end of the second sliding rod 23 is inserted into the sleeve 22. The other end of the second sliding rod 23 is movably screwed onto the lower part of the pad 21. Inside the wall, four pairs of the second springs 24 are movably mounted on the second slide rod 23, with one end of the second spring 24 movably inserted into the sleeve 22 and the other end of the second spring 24 attached to the upper wall of the pressure relief frame 11. The pressure relief is achieved by the pressure of the pad plate 21 being pressed down by the gravity of the fuselage during landing, which compresses the second springs 24 mounted on the second slide rod 23. At the same time, since the sleeve 22 is provided under the pad plate 21, the second spring 24 is compressed to the maximum extent that the sleeve 22 contacts the pressure relief frame 11, ensuring that the pad plate 21 is located above the pressure relief frame 11 and has a certain height to support the fuselage.

[0034] As a further embodiment of the present invention, the anti-collision structure 3 includes a mounting ring 31, four pairs of rotating rollers 32, four pairs of protective claws 33, several first connecting rods 34, several second connecting rods 35, a center platform 36, a motor 37, a pulley 38, a transmission belt 39, and two pairs of retaining ring assemblies 40; the mounting ring 31 is a circular ring structure, and the four pairs of rotating rollers 32 are equidistantly mounted on the mounting ring 31. All four pairs of rotating rollers 32 rotate around the mounting ring 31 and cannot move left or right. One end of each rotating roller 32 has a groove 5 on its outer side wall. All four pairs of protective claws 33 are arc-shaped, and one end of each pair of protective claws 33 is fixedly mounted on... On the side wall of the rotating roller 32, with the inner wall of the protective claw 33 facing upwards, one end of several first connecting rods 34 are movably connected to the upper walls of both ends of the rotating roller 32, and the two ends of several second connecting rods 35 are movably connected between the other ends of the first connecting rods 34, with the second connecting rods 35 located inside the mounting ring 31. One end of the center platform 36 is fixedly fitted onto the mounting ring 31, and one end of the center platform 36 is located near one of the rotating rollers 32. The other end of the center platform 36 is circular and located at the center of the mounting ring 31. The motor 37 is fixedly mounted on the lower wall of one end of the center platform 36, and the motor 37 is provided with a converter. The pulley 38 is fixedly mounted on the drive end of the motor 37, and the pulley 38 corresponds to the 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 groove 5 of one of the rollers 32, respectively. Two pairs of retaining 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 via the retaining ring assemblies 40, or fixed to the belly of the fuselage via the center platform 36. In use, the motor 37 is connected to the fuselage and powered on. The controller of the drone controls the rotation of the motor 37, which in turn drives the pulley 38 to rotate. The transmission belt 39 drives one of the rollers 32 to rotate on the mounting ring 31. Through the connection between the second connecting rod 35 and the first connecting rod 34 between the two rollers 32, a series linkage is achieved, which drives the roller 32 to rotate on the mounting ring 31 at the same time, thereby causing the protective claw 33 to flip. When landing, the protective claw 33 flips outward and is located outside the pressure relief structure 1. When the support leg 12 is subjected to force and flips to a certain extent, as the pressure relief frame 11 and the pad 21 drop to a certain height, the other end of the protective claw 33 contacts the ground to provide auxiliary support and ensure landing stability. After takeoff, the protective claw 33 flips relative to the outside of the fuselage to shield and prevent collision.

[0035] As a further embodiment of the present invention, the center platform 36 is detachably mounted on the pad 21 by bolts to meet the design and installation requirements, enabling the anti-collision structure 3 to be directly used on UAVs for landing support and takeoff protection.

[0036] As a further embodiment of the present invention, the retaining ring assembly 40 is composed of a pair of relatively mating semi-circular retaining claws that are movably connected to each other, and the other end is fixed relative to each other by bolts. One of the retaining claws in the retaining ring assembly 40 is provided with a docking plate connected to the center platform 36 on its lower wall. This is a prior art structure that facilitates fixing to the existing landing gear rod.

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

[0038] As a further embodiment 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 simultaneously contact the ground, which is used to design an auxiliary landing to increase stability.

[0039] Its detailed connection method is a well-known technology in this field. The following mainly introduces the working principle and process, and the specific work is as follows.

[0040] First, the retaining ring assembly 40 in the anti-collision structure 3 is connected and installed to the existing bottom landing gear rod of the drone. Alternatively, the retaining ring assembly 40 can be removed as needed and connected to the drone fuselage via the center console 36. At the same time, the adapter cable of the motor 37 is connected to the drone and controlled by the controller.

[0041] During use, the drone is supported by the feet 12 in the pressure relief structure 1 in contact with the ground, and the height of the supported fuselage is increased by the height-increasing component 2, which is conducive to the airflow generated during the take-off of the drone.

[0042] After the drone takes off, the control motor 37 drives the pulley 38 to rotate, which causes the transmission belt 39 to drive one of the rollers 32 to rotate on the mounting ring 31. 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 rotate synchronously on the mounting ring 31 at the corresponding angle. This allows the protective claw 33 to be flipped relative to each other and placed outside the propeller of the drone body to form a shield and protection, avoiding damage to the propeller and fuselage from impacts 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 leg 12 is the first to contact the ground and bear the force. The weight of the drone will be applied to the pad 21 in the height-increasing component 2. The pad 21 will descend under the force and compress the second spring 24, which is limited by the second slide rod 23. The second spring 24 will provide pressure relief and buffering. At the same time, the descent height of the pad 21 is limited, up to the point that the sleeve 22 contacts the pressure relief frame 11. The sleeve 22 will maintain the pad 21 at a certain height to support the fuselage.

[0044] Then the weight of the fuselage will be applied to the pressure relief frame 11. As the pressure relief frame 11 is lowered by the force, it will cause the support leg 12 to rotate at a certain angle. At the same time, the rotation of the support leg 12 will pull the first baffle 15 through the linkage rod 17. Then the first baffle 15 is subjected to force and moves on the first slide rod 14 through the shield of the frame 13 to compress the first spring 16. The first spring 16 will buffer and relieve pressure on the support leg 12 and the pressure relief frame 11 to prevent impact damage due to the drop in weight.

[0045] When landing, if the protective claw 33 is flipped to the outside of the pressure relief structure 1, the pressure relief frame 11 will be lowered and the pad 21 will also be lowered to a certain height as the support leg 12 flips and buffers. As a result, the other end of the protective claw 33 will contact the ground as the height decreases, assisting the support leg 12 in providing stable support.

[0046] When landing, if the protective claw 33 does not flip over and is located outside the pressure relief structure 1, it will always be located outside the fuselage to provide shielding and protection, ensuring effective protection if the fuselage tilts during landing.

[0047] The aforementioned anti-collision structure 3 can be directly installed on the fuselage via the center platform 36, and supports the fuselage by the reverse flipping of the protective claws 33. After takeoff, it flips relative to the fuselage for protection.

[0048] 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 landing gear for an unmanned aerial vehicle (UAV) equipped with a flight collision avoidance and pressure relief structure, characterized in that: It includes a pressure relief structure (1), a height-increasing component (2), and a collision protection structure (3); the height-increasing component (2) is movably mounted on the pressure relief structure (1), and the collision protection structure (3) is detachably mounted on the height-increasing component (2); The anti-collision structure (3) includes a mounting ring (31), four pairs of rotating rollers (32), four pairs of protective claws (33), several first connecting rods (34), several second connecting rods (35), a center platform (36), a motor (37), a pulley (38), a transmission belt (39), and two pairs of retaining ring assemblies (40); The mounting ring (31) is a circular ring structure. Four pairs of rotating rollers (32) are equidistantly mounted on the mounting ring (31). All four pairs of rotating rollers (32) rotate around the mounting ring (31) and cannot move left or right. One of the rotating rollers (32) has a groove (5) on its outer side wall. All four pairs of protective claws (33) are arc-shaped. One end of each of the four pairs of protective claws (33) is fixedly set on the side wall of the rotating roller (32), and the inner side wall of the protective claws (33) faces upward. One end of each of the first connecting rods (34) is movably connected to the upper walls of both ends of the rotating roller (32). The two ends of each of 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 inside the mounting ring (31). The central platform (36) One end is fixedly fitted onto the mounting ring (31) and one end of the center platform (36) is located near one of the rotating rollers (32). The other end of the center platform (36) is circular and located in the center of the mounting ring (31). The motor (37) is fixedly installed on the lower wall of one end of the center platform (36) and is provided with a conversion cable. The pulley (38) is fixedly fitted onto the drive end of the motor (37) and corresponds to the groove (5) of one of the rotating rollers (32). The two ends of the transmission belt (39) are respectively movably fitted onto the pulley (38) and the groove (5) of one of the rotating rollers (32). The two pairs of retaining ring assemblies (40) are respectively detachably installed on the upper wall of the center platform (36). The pressure relief structure (1) includes a pressure relief frame (11), two pairs of support legs (12), two pairs of frames (13), two pairs of first slide rods (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 with symmetrical telescopic holes near the four corners. One end of each of the two pairs of support legs (12) is movably mounted in the middle of the side wall of the pressure relief frame (11), and the support legs (12) are inclined in four directions. Both pairs of frames (13) are concave structures, and 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 support legs (12). One end of each of the two pairs of first sliding rods (14) movably passes through the middle of the side wall of the frame (13) and is screwed onto the pressure relief frame. Inside the inner wall of the pressure frame (11), two pairs of first baffles (15) are movably embedded in the frame (13), and the first baffles (15) are movably mounted on the first slide rod (14). Two pairs of first springs (16) are movably mounted on the first slide rod (14), and the first springs (16) are located between the first baffles (15) and the pressure relief frame (11). One end of each pair of connecting rods (17) is movably connected to the middle of the lower wall of the support leg (12), and the other end of each connecting rod (17) is movably connected to the middle of the lower wall of the first baffle (15). The height-increasing component (2) includes a pad (21), four pairs of sleeves (22), four pairs of second slide rods (23), and four pairs of second springs (24); The pad (21) is rectangular in structure and is movably mounted above the pressure relief frame (11). 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 each of the four pairs of second slide rods (23) is movably inserted through the telescopic hole of the pressure relief frame (11), and the other end of the second slide rod (23) is inserted into the sleeve (22). The other end of the second slide rod (23) is movably screwed into the lower wall of the pad (21). Four pairs of second springs (24) are movably mounted on the second slide rods (23), and one end of the second spring (24) is movably inserted into the sleeve (22). The other end of the second spring (24) is attached to the upper wall of the pressure relief frame (11).

2. The landing gear for a UAV equipped with a flight anti-collision and pressure relief structure according to claim 1, characterized in that: The central platform (36) is detachably mounted on the pad (21) by bolts.

3. The landing gear for a UAV equipped with a flight anti-collision and pressure relief structure according to claim 2, characterized in that: The retaining ring assembly (40) consists of a pair of relatively mating semi-circular retaining claws that are movably connected to each other, and the other end is fixed relative to each other by bolts. A docking plate connected to the central platform (36) is provided on the lower wall of one of the retaining claws in the retaining ring assembly (40).

4. The landing gear for a UAV equipped with a flight anti-collision and pressure relief structure according to claim 3, characterized in that: The first link (34) and the second link (35) are both located outside the pad (21) and cannot contact the pad (21).

5. The landing gear for a UAV equipped with a flight anti-collision and pressure relief structure according to claim 4, characterized in that: 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 simultaneously contact the ground.

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