A drone landing buffer device

Abstract

This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a UAV landing buffer device. It includes a UAV; a landing gear is installed on the bottom of the UAV; the landing gear includes a cross plate; rectangular rods are fixed to the bottom ends of the four plates on the cross plate; rectangular cylinders are provided at the bottom of the rectangular rods; two inclined plates are provided on opposite sides of the two base plates; each inclined plate has a convex groove; a convex block slides in each convex groove; a connecting plate rotates on the top of each convex block; two circular grooves are provided inside each convex block; a gear rotates unidirectionally in each circular groove; a rotating rod is provided below the convex block; evenly arranged arc-shaped teeth are fixed on the side of the rotating rod facing the gear. This invention, by setting up the landing gear, can solve the defects of traditional fixed elastic landing gear, such as limited energy absorption capacity and no attenuation of impact overload transmitted to the fuselage under hard landing conditions.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a UAV landing buffer device. Background Technology

[0002] With the rapid development of drone technology, multi-rotor drones, with their advantages of vertical takeoff and landing, flexibility, and ease of operation, have been widely used in various fields such as consumer-grade aerial photography, power line inspection, emergency rescue, geographic surveying, and agricultural and forestry plant protection, becoming one of the core equipment of the low-altitude economy industry. In the entire flight process of a drone, the landing phase is a high-risk stage for flight accidents. Factors such as near-ground effect, crosswind turbulence, positioning accuracy errors, and insufficient adaptability to complex terrain can easily lead to accidents such as hard landings, loss of attitude control, and aircraft rollover.

[0003] Currently, there are corresponding technical solutions in the industry for drone landing cushioning. In terms of passive cushioning structures, the most common is the fixed elastic landing gear, which is made of elastic materials such as carbon fiber, engineering plastics, and rubber. It relies on the deformation of the material itself to absorb the impact of landing. With its advantages of simple structure and lightweight, it is widely used in consumer-grade small drones. For medium and large industrial drones, the industry mostly uses hydraulic or pneumatic damping landing gear, which dissipates impact energy through fluid damping, has a larger cushioning stroke and energy absorption efficiency, and can be adapted to the strong impact scenarios of drones with large payloads.

[0004] Because the core components of the drone, such as the gimbal camera, inertial measurement unit, flight control chip, and lidar, are all high-precision sensitive devices, they are extremely sensitive to impact overload. The rigid impact generated by a hard landing can easily cause permanent damage to the components, or even cause the entire aircraft to be scrapped. The existing fixed flexible landing gear has limited energy absorption capacity. When the UAV experiences excessive sinking rate or hard landing due to wind disturbance or positioning errors, it cannot effectively dissipate rigid impact energy. The impact overload will be directly transmitted to the fuselage and onboard precision equipment, which can easily cause irreversible damage such as damage to the gimbal camera's image stabilization structure, zero-point drift of the inertial measurement unit, detachment of flight control solder joints, and failure of sensor accuracy. In severe cases, it can also lead to deformation of motor bearings, cracking of the carbon fiber structure of the arms, or even scrapping the entire aircraft. At the same time, there is a high risk of significant rebound after the landing gear touches the ground. Combined with the ground effect, the rebound process can easily cause serious safety accidents such as fuselage rollover or high-speed rotating propellers hitting the ground and causing the aircraft to explode. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies and solve the aforementioned technical problems, this invention proposes a landing buffer device for unmanned aerial vehicles (UAVs). By incorporating landing gear, it can overcome the limitations of traditional fixed elastic landing gear in terms of limited energy absorption capacity and the lack of attenuation in transmitting impact overload to the fuselage under hard landing conditions. The specific structure is as follows: A drone landing buffer device includes a drone; the drone is equipped with landing gear at its bottom; The landing gear includes a cross plate; the cross plate is fixed to the bottom of the UAV, and the four plates of the cross plate extend between two adjacent propellers on the UAV. The bottom ends of the four plates on the cross plate are all fixed with rectangular rods; the bottom of the rectangular rods is provided with rectangular tubes, and the rectangular rods slide inside the rectangular tubes and cannot slide out from the top of the rectangular tubes; The bottoms of the two rectangular tubes located on the same side are jointly fitted with a base plate; each rectangular tube is equipped with a spring, and the spring is located at the bottom of the rectangular tube; Two inclined plates are provided on opposite sides of the two base plates, and the inclined plates are fixed on opposite rectangular tubes respectively; each of the inclined plates has a convex groove inside, and the convex groove penetrates through the top of the inclined plate; Each of the convex grooves has a convex block sliding inside it; each of the convex blocks has a connecting plate rotating on its top, and the other side of the connecting plate rotates on the top of the rectangular rod and is located below the cross plate. Each of the convex blocks has two circular grooves inside, and the two circular grooves penetrate the bottom of the convex block; each of the circular grooves has a gear that rotates in one direction, and the gear part extends to the bottom of the convex block; A rotating rod is provided below the convex block; the rotating rod has evenly arranged arc-shaped teeth fixed on the side facing the gear, and the arc-shaped teeth mesh with the gear; Below the convex block, a cylindrical groove is formed inside the inclined plate, and the rotating rod and the arc-shaped tooth both rotate within the cylindrical groove; a motor is installed on the side of the rotating rod facing the rectangular tube.

[0006] In a preferred embodiment of the present invention, each of the rectangular rods is provided with a through hole; A vertical rod slides within the through hole, with its top extending through the cross plate to above it and slidably connected to it; the bottom of the vertical rod extends to the bottom of the rectangular tube. Each of the uprights is equipped with a horizontal plate at the top; a protective ring is fixed to the outer ring of multiple horizontal plates, and the rotation range of the propeller on the UAV is located within the inner ring of the protective ring, and does not contact the protective ring.

[0007] In a preferred embodiment of the present invention, the bottom of the protective ring is fixedly fitted with uniformly arranged protective rods.

[0008] In a preferred embodiment of the present invention, a limiting ring is fixed to one side of the upright extending above the cross plate; the top of the limiting ring is provided with threads on the upright. The horizontal plate has a circular groove, and the circular groove on the horizontal plate is fitted onto the upright above the limiting ring; a nut is provided above each circular groove, and the nut is used to lock the horizontal plate.

[0009] In a preferred embodiment of the present invention, the bottom of the rectangular tube is provided with a cap, and the cap is fixed to the rectangular tube by bolts; The top of the cover has a groove, and the upright rotates within the groove; The cover is located on the base plate and is fixed to the base plate by bolts.

[0010] In a preferred embodiment of the present invention, a rectangular block slides inside the rectangular tube; The rectangular block has a threaded groove in the middle, and the upright rod passes through the threaded groove and rotates in the groove; the spring inside the rectangular tube is located above the rectangular block; The bottom of the upright is threaded, and the thread engages with the threaded groove.

[0011] In a preferred embodiment of the present invention, each of the convex blocks is fixed with an extension plate on the side away from the rectangular tube; The extension plate extends out from the convex groove.

[0012] In a preferred embodiment of the present invention, the two extension plates located on the same side extend out of the convex groove and are connected and fixed by a connecting plate.

[0013] In a preferred embodiment of the present invention, each of the extension plates is provided with a sliding groove. An adjusting plate slides within the groove; a spring is provided on the adjusting plate, and the other side of the spring is fixed within the groove.

[0014] The beneficial effects of this invention are as follows: 1. The UAV landing buffer device of the present invention, during the UAV's ground contact buffering process, a rectangular rod slides along the axial direction of a rectangular cylinder and compresses the built-in spring. Through the elastic deformation of the spring, the kinetic energy of the UAV's vertical descent is converted into elastic potential energy, which significantly prolongs the impact time and significantly weakens the impact load on the ground. This solves the defects of traditional fixed elastic landing gear in terms of limited energy absorption capacity and the lack of attenuation of impact overload to the UAV under hard landing conditions. It effectively avoids irreversible damage such as damage to the gimbal camera's image stabilization structure, zero-point drift of the inertial measurement unit, detachment of flight control solder joints, and sensor accuracy failure. At the same time, it eliminates structural damage such as deformation of motor bearings and cracking of the carbon fiber structure of the arm caused by impact load, greatly reducing the risk of scrapping the entire aircraft and extending the service life of the UAV equipment.

[0015] 2. The UAV landing buffer device of the present invention, during the buffering process of the rectangular rod compressing the spring as the UAV moves downward, simultaneously pushes the convex block along the convex groove of the inclined plate through the connecting plate, driving the one-way gear to rotate along the arc tooth meshing; when the buffering stroke reaches the limit position, the one-way rotating gear and the arc tooth form a reverse rigid lock, fixing the position of the convex block, and then restricting the upward rebound of the rectangular rod under the spring reaction force through the connecting plate, completely eliminating the risk of landing gear rebound; this structure avoids serious safety accidents such as fuselage attitude imbalance, rollover, and high-speed rotating blades hitting the ground and destroying the aircraft during the rebound process, and greatly improves the attitude stability and safety of the UAV landing process.

[0016] 3. The UAV landing buffer device described in this invention, during the UAV's ground contact buffering process, when the rectangular rod slides downward along the rectangular cylinder, it will drive the cross plate and the UAV body to move downward synchronously. At the same time, the rectangular rod slides along the axial direction of the upright, and the upright gradually extends from the top of the rectangular rod, allowing the UAV body and propeller to gradually enter the inner ring of the protective ring and the protective rod. Because the protective ring is precisely adapted to the propeller's rotation range, it ensures that the propeller rotates normally without interference, while achieving all-round protection for the fuselage and propeller. When the UAV rolls over due to wind disturbance or attitude deviation, the protective ring and the evenly distributed protective rods at the bottom will preferentially contact the ground, forming a rigid protective barrier to prevent the UAV body and propeller from directly impacting the ground. This not only prevents the fuselage structure from cracking and the onboard equipment from being damaged, but also eliminates the risk of the UAV crashing due to the propeller hitting the ground or breaking off the propeller, further improving the safety of UAV landing. Attached Figure Description

[0017] The invention will now be further described with reference to the accompanying drawings.

[0018] Figure 1 This is a state diagram of the overall state of the UAV and landing gear of this invention; Figure 2 This is a diagram showing the state of the UAV and landing gear after the protective rings have been installed. Figure 3 This is a structural diagram of the landing gear of the present invention; Figure 4 This is a structural diagram of the rectangular rod and rectangular tube in this invention; Figure 5 This is a diagram showing the internal structure of the rectangular rod and rectangular tube in this invention; Figure 6 This is the present invention. Figure 5 Enlarged view of a portion of point A in the middle; Figure 7 This is the present invention. Figure 2 Top view; Figure 8 This is the present invention. Figure 7 Sectional view at point BB; Figure 9 This is the present invention. Figure 8 Enlarged view of a section at point C; Figure 10 This is the present invention. Figure 8 Enlarged view of a section at point D; Figure 11 This is the present invention. Figure 8 Enlarged view of a section at point E in the middle.

[0019] In the diagram: 1. Cross plate; 11. Rectangular rod; 12. Rectangular cylinder; 13. Base plate; 2. Inclined plate; 21. Convex groove; 22. Convex block; 23. Connecting plate; 24. Circular groove; 25. Gear; 26. Rotating rod; 27. Arc tooth; 28. Columnar groove; 3. Upright rod; 31. Horizontal plate; 32. Protective ring; 33. Protective rod; 34. Limiting ring; 35. Nut; 4. Cover; 41. Groove; 42. Rectangular block; 5. Extension plate; 51. Connecting plate; 52. Slide groove; 53. Adjusting plate. Detailed Implementation

[0020] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with specific embodiments.

[0021] like Figures 1 to 11 As shown, the UAV landing buffer device of the present invention, as an embodiment of the present invention, includes a UAV; the UAV is equipped with landing gear at its bottom; The landing gear includes a cross plate 1; the cross plate 1 is fixed to the bottom of the UAV, and the four plates of the cross plate 1 extend to the space between two adjacent propellers on the UAV. A rectangular rod 11 is fixed to the bottom of each of the four plates on the cross plate 1; a rectangular tube 12 is provided at the bottom of the rectangular rod 11, and the rectangular rod 11 slides inside the rectangular tube 12, and the rectangular rod 11 cannot slide out from the top of the rectangular tube 12. The bottom of the two rectangular tubes 12 located on the same side is jointly installed with a base plate 13; each rectangular tube 12 is provided with a spring, and the spring is located at the bottom of the rectangular rod 11; Two inclined plates 2 are provided on opposite sides of the two base plates 13, and the inclined plates 2 are respectively fixed on the opposite rectangular tubes 12; each of the inclined plates 2 has a convex groove 21, and the convex groove 21 penetrates the top of the inclined plate 2. Each of the convex grooves 21 has a convex block 22 sliding inside it; each of the convex blocks 22 has a connecting plate 23 rotating on its top, and the other side of the connecting plate 23 rotates on the top of the rectangular rod 11 and is located below the cross plate 1. Each of the convex blocks 22 has two circular grooves 24 inside, and the two circular grooves 24 penetrate through the bottom of the convex block 22; each of the circular grooves 24 has a unidirectional rotating gear 25 inside, and the gear 25 extends to the bottom of the convex block 22. A rotating rod 26 is provided below the convex block 22; the rotating rod 26 has evenly arranged arc-shaped teeth 27 fixed on the side facing the gear 25, and the arc-shaped teeth 27 mesh with the gear 25. Below the convex block 22, a cylindrical groove 28 is provided in the inclined plate 2, and the rotating rod 26 and the arc-shaped tooth 27 both rotate within the cylindrical groove 28; a motor is installed on the side of the rotating rod 26 facing the rectangular tube 12.

[0022] After the UAV completes its high-altitude operation and receives the landing command, it descends vertically to the preset landing point at a stable rate. As the UAV descends, it drives the entire landing gear to descend gradually. When the landing gear makes direct contact with the ground, the impact load on the landing gear will act on the base plate 13 and the rectangular tube 12. At this time, the base plate 13 remains stationary due to ground support and no longer moves downward, while the UAV continues to move downward due to inertia. This causes the rectangular rod 11, which is fixedly connected to the UAV, to slide downward along the inner cavity of the rectangular tube 12, while simultaneously generating axial compression on the spring inside the rectangular tube 12. During the compression process, the spring undergoes elastic deformation, converting the vertical descent kinetic energy of the UAV fuselage into its own elastic potential energy, thereby buffering the impact of the landing UAV, effectively reducing the peak value of the ground impact load, lengthening the impact time, reducing the impact overload transmitted to the main body of the UAV fuselage, and avoiding damage to the fuselage structure, gimbal camera, high-precision sensors, and other core components caused by a hard landing.

[0023] Specifically, when the rectangular rod 11 slides downward along the rectangular tube 12, it drives the connecting plate 23 to move downward. Since the two ends of the connecting plate 23 rotate on the rectangular rod 11 and the convex block 22 respectively, when the rectangular rod 11 drives the connecting plate 23 to move downward, the connecting plate 23 pushes the convex block 22 to slide downward in the convex groove 21 of the inclined plate 2. During the downward sliding of the convex block 22, it drives the gear 25 inside the convex block 22 to move downward. Since the gear 25 is initially engaged with the arc-shaped tooth 27, it will rotate during the movement of the convex block 22 along the arc-shaped tooth 27. Since the gear 25 rotates in one direction, it will not reverse direction after rotating along the arc-shaped tooth 27. When the rectangular rod 11... After the rectangular tube 12 moves down to its limit position, the convex block 22 also stops sliding. At this point, the gear 25, which will not reverse, will be fixed by the arc-shaped tooth 27. Therefore, the position of the convex block 22 can be fixed. After the position of the convex block 22 is fixed, the position of the rectangular rod 11 moving down into the rectangular tube 12 is also fixed. Therefore, the rectangular rod 11, after sliding down, will not rebound under the reaction force of the spring. This will prevent the drone from tipping over or crashing after the landing gear rebounds. At the same time, since the ramp 2 extends to both sides of the base plate 13, if the drone tilts to both sides during landing, the ramp 2 can support the ground, thereby preventing the drone from tipping over.

[0024] More specifically; when the drone needs to perform high-altitude operations, control the drone to take off; after the drone takes off, control the motor to drive the rotating rod 26 to rotate 180 degrees. The rotating rod 26 will drive the arc-shaped tooth 27 to rotate 180 degrees in the cylindrical groove 28. After the rotating rod 26 drives the arc-shaped tooth 27 to rotate 180 degrees, the arc-shaped tooth 27 rotates to below the rotating rod 26 and is no longer engaged with the gear 25. At this time, the convex block 22 is no longer fixed. Under the action of the spring, it will push the rectangular rod 11 to return to its initial state. At the same time, it will drive the convex block 22 to return to its initial state in the convex groove 21 through the connecting plate 23. When the drone lands again, the above operation is repeated.

[0025] In summary, during the drone's ground contact buffering process, the rectangular rod 11 slides along the axial direction of the rectangular tube 12 and compresses the built-in spring. Through the elastic deformation of the spring, the kinetic energy of the drone's vertical descent is converted into elastic potential energy, significantly extending the impact time and significantly weakening the ground contact impact load. This solves the defects of traditional fixed elastic landing gear, such as limited energy absorption capacity and no attenuation of impact overload transmitted to the drone under hard landing conditions. It effectively avoids irreversible damage such as damage to the gimbal camera's image stabilization structure, zero-point drift of the inertial measurement unit, detachment of flight control solder joints, and sensor accuracy failure. At the same time, it eliminates structural damage such as motor bearing deformation and cracking of the carbon fiber structure of the arm caused by impact load, greatly reducing the risk of scrapping the entire drone and extending the service life of the drone equipment.

[0026] Simultaneously, during the buffering process of the rectangular rod 11 compressing the spring as the UAV moves downward, the connecting plate 23 pushes the convex block 22 to slide along the convex groove 21 of the inclined plate 2, driving the one-way gear 25 to mesh and rotate along the arc tooth 27. When the buffering stroke reaches the limit position, the one-way rotating gear 25 and the arc tooth 27 form a reverse rigid lock, fixing the position of the convex block 22. Then, the connecting plate 23 restricts the upward rebound of the rectangular rod 11 under the spring reaction force, completely eliminating the risk of landing gear rebound. This structure avoids serious safety accidents such as fuselage attitude imbalance, rollover, and high-speed rotating propellers hitting the ground and destroying the aircraft during the rebound process, and greatly improves the attitude stability and safety of the UAV during the landing process.

[0027] As an embodiment of the present invention; each of the rectangular rods 11 has a through hole; a vertical rod 3 slides in the through hole, and the top of the vertical rod 3 extends through the cross plate 1 to the top of the cross plate 1 and is slidably connected to the cross plate 1; the bottom of the vertical rod 3 extends to the bottom of the rectangular tube 12; a horizontal plate 31 is installed on the top of each vertical rod 3; a protective ring 32 is fixed to the outer ring of the multiple horizontal plates 31, and the rotation range of the propeller on the UAV is located in the inner ring of the protective ring 32 and does not contact the protective ring 32.

[0028] In this embodiment, the bottom of the protective ring 32 is fixedly equipped with uniformly arranged protective rods 33.

[0029] In this embodiment, a limiting ring 34 is fixed to one side of the upright 3 extending above the cross plate 1; the upright 3 at the top of the limiting ring 34 is threaded.

[0030] The horizontal plate 31 has a circular groove 24, and the circular groove 24 on the horizontal plate 31 is fitted onto the upright 3 above the limiting ring 34; a nut 35 is provided above each circular groove 24, and the nut 35 is used to lock the horizontal plate 31.

[0031] Because the rectangular rod 11 has sliding uprights 3 inside, and the tops of multiple uprights 3 are fixed with protective rings 32 by horizontal plates 31; when the rectangular rod 11 slides downward inside the rectangular tube 12, it will drive the drone downward through the cross plate 1, and at the same time, the downward sliding rectangular rod 11 will slide down along the uprights 3. At this time, the uprights 3 gradually extend from the top of the rectangular rod 11; and the downward-moving drone will gradually move down to the inner circle of the protective ring 32. Since the rotation range of the helicopter's propeller is located within the inner circle of the protective ring 32, it will not affect the rotation of the propeller; when the drone and propeller move down to the protective ring 32, the drone will move down to the inner circle of the protective ring 32. When the inner ring 32 is in place, the protective ring 32 can protect the drone. At the same time, since the bottom of the protective ring 32 is fixed with evenly distributed protective rods 33, multiple protective rods 33 can protect the outer ring of the drone and propeller. If the drone rolls over during landing, the protective ring 32 and protective rods 33 will contact the ground first, thus preventing the drone body and propeller from directly contacting the ground. This can prevent the drone from being damaged by an impact and also prevent the propeller from contacting the ground and hitting the ground.

[0032] Specifically, since the horizontal plate 31 is fitted onto the vertical pole 3 and fixed by the nut 35, when using the drone, the protective ring 32 can be selectively used or not. If the protective ring 32 is not used, the nut 35 is removed from the top of the vertical pole 3, and then the horizontal plate 31 is removed from the vertical pole 3, thereby removing the protective ring 32.

[0033] In summary, during the drone's ground contact and buffering process, as the rectangular rod 11 slides downward along the rectangular tube 12, it causes the cross plate 1 and the drone body to move downward synchronously. At the same time, the rectangular rod 11 slides along the axis of the upright rod 3, and the upright rod 3 gradually extends from the top of the rectangular rod 11, allowing the drone body and propeller to gradually enter the inner circle of the protective ring 32 and the protective rod 33. Since the protective ring 32 is precisely adapted to the propeller's rotation range, it ensures that the propeller rotates normally without interference, while achieving all-round protection for the fuselage and propeller. When the drone rolls over due to wind disturbance or attitude deviation, the protective ring 32 and the evenly distributed protective rods 33 at the bottom will make priority contact with the ground, forming a rigid protective barrier to prevent the drone body and propeller from directly impacting the ground. This not only prevents the fuselage structure from cracking and the onboard equipment from being damaged, but also eliminates the risk of the drone crashing due to the propeller hitting the ground or breaking off the propeller, further improving the safety of the drone landing.

[0034] As one embodiment of the present invention; the bottom of the rectangular tube 12 is provided with a cover 4, and the cover 4 is fixed to the rectangular tube 12 by bolts; The top of the cover 4 is provided with a groove 41, and the upright 3 rotates within the groove 41; The cover 4 is located on the base plate 13 and is fixed to the base plate 13 by bolts; In this embodiment, a rectangular block 42 slides inside the rectangular tube 12; The rectangular block 42 has a threaded groove in the middle, and the upright rod 3 passes through the threaded groove and rotates in the groove 41; the spring in the rectangular tube 12 is located above the rectangular block 42. The bottom of the upright 3 is threaded, and the thread engages with the threaded groove.

[0035] Since the spring is located above the rectangular block 42, and the threaded groove on the rectangular block 42 engages with the thread at the bottom of the upright 3, controlling the rotation of the upright 3 can drive the rectangular block 42 to move upward. The upward movement of the rectangular block 42 will push the spring upward. Since the position of the top of the spring remains unchanged, the overall length of the spring becomes shorter, causing the spring to enter a pre-compressed state. This reduces the effective buffering stroke of the spring. When the UAV moves the rectangular rod 11 downward, the travel distance of the rectangular rod 11 from downward to stop is shortened, thereby changing the downward movement of the rectangular rod 11 when the UAV moves it for landing buffering. This allows for flexible adjustment of the spring length according to the actual takeoff weight, payload, and operating scenario of the UAV. That is, under heavy load conditions, the pre-compression of the spring is increased to improve buffering stiffness; under light load conditions, the pre-compression is reduced to release the effective buffering stroke, ensuring buffering smoothness and perfectly adapting to the landing buffering requirements under different loads and operating conditions.

[0036] Specifically, since the bottom of the rectangular tube 12 is bolted with a cover 4 and the cover 4 is fixed to the base plate 13 by bolts, when the spring needs to be replaced, the base plate 13 is removed from the cover 4, and the cover 4 is removed from the bottom of the rectangular tube 12. Then the upright rod 3 is rotated in the opposite direction, and the upright rod 3 will push the rectangular block 42 down and gradually detach it from the rectangular tube 12. After the rectangular block 42 is detached from the rectangular tube 12, the spring can be removed and a new spring can be replaced. At the same time, the rectangular rod 11 and the upright rod 3 can be taken out from the bottom of the rectangular tube 12 for inspection or replacement.

[0037] As an embodiment of the present invention, each of the convex blocks 22 is fixed with an extension plate 5 on the side away from the rectangular tube 12; the extension plate 5 extends out from the convex groove 21.

[0038] In this embodiment, the two extension plates 5 located on the same side extend out of the convex groove 21 and are connected and fixed by a connecting plate 51.

[0039] In this embodiment, each of the extension plates 5 is provided with a sliding groove 52; an adjustment plate 53 slides in the sliding groove 52; a spring is provided on the adjustment plate 53, and the other side of the spring is fixed in the sliding groove 52.

[0040] Since the extension plate 5 is fixed on the convex block 22, when the convex block 22 slides along the convex groove 21, it will drive the extension plate 5 to gradually extend. The extended plate 5 can increase the extension range and get closer to the ground. When the drone rolls over, the extension plate 5 can make contact with the ground earlier, thereby preventing the drone from rolling over. At the same time, since the adjustment plate 53 slides inside the extension plate 5 through the spring, when the convex block 22 drives the extension plate 5 to extend out of the convex groove 21, if the adjustment plate 53 first contacts a stone or debris of a certain height nearby, the adjustment plate 53 will slide into the slide groove 52, thereby preventing the adjustment plate 53 from hitting the stone or debris and preventing the convex block 22 from continuing to slide in the convex groove 21.

[0041] Specifically, since the two adjacent extension plates 5 are connected by the connecting plate 51, when the UAV is landing, if one of the rectangular tubes 12 contacts the ground first, the presence of the connecting plate 51 will cause the convex block 22 inside the other inclined plate 2 that is not in contact with the ground to move. At the same time, it will cause the other rectangular rod 11 that is not in contact with the ground to gradually slide into the rectangular tube 12. This will ensure that the two rectangular rods 11 on the same side are in the same state when they move down, ensuring that the buffering action of the rectangular rods 11 and the rectangular tube 12 on the same side is synchronized and the force is even. This avoids the problem of inconsistent downward movement and asynchronous speed of the two rectangular rods 11 on the same side due to one-sided contact with the ground and imbalance of force, thereby preventing the fuselage from tilting to one side and shifting the center of gravity. This avoids the risk of the fuselage tipping over due to excessive sinking on one side.

[0042] In the description of this invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the appendix. Figure 1 The orientations or positional relationships shown are for the convenience of describing the present invention and simplifying the description only, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of the present invention. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description and should not be construed as indicating or implying relative importance.

[0043] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A drone landing buffer device, comprising a drone; the drone is equipped with landing gear at its bottom; Its features are, The landing gear includes a cross plate (1); the cross plate (1) is fixed to the bottom of the UAV; Rectangular rods (11) are fixed to the bottom ends of the four plates on the cross plate (1); The rectangular rod (11) has a rectangular tube (12) at its bottom, and the rectangular rod (11) slides inside the rectangular tube (12); The bottom of the two rectangular tubes (12) located on the same side is jointly installed with a base plate (13); each rectangular tube (12) is provided with a spring, and the spring is located at the bottom of the rectangular rod (11); Two inclined plates (2) are provided on opposite sides of the two base plates (13), and the inclined plates (2) are fixed on opposite rectangular tubes (12); each of the inclined plates (2) is provided with a convex groove (21); Each of the convex grooves (21) has a convex block (22) sliding inside it; each of the convex blocks (22) has a connecting plate (23) rotating on its top, and the other side of the connecting plate (23) rotates on the top of the rectangular rod (11); Each of the convex blocks (22) has two circular grooves (24) inside, and the two circular grooves (24) penetrate the bottom of the convex block (22); each of the circular grooves (24) has a gear (25) that rotates in one direction, and the gear (25) extends to the bottom of the convex block (22); A rotating rod (26) is provided below the convex block (22); the rotating rod (26) has evenly arranged arc-shaped teeth (27) fixed on the side facing the gear (25), and the arc-shaped teeth (27) mesh with the gear (25); The convex block (22) has a cylindrical groove (28) inside the inclined plate (2) below it, and the rotating rod (26) and the arc-shaped tooth (27) both rotate in the cylindrical groove (28); a motor is installed on the side of the rotating rod (26) facing the rectangular tube (12).

2. The UAV landing buffer device according to claim 1, characterized in that: Each of the rectangular rods (11) has a through hole; A vertical rod (3) slides inside the through hole, and the top of the vertical rod (3) extends through the cross plate (1) to the top of the cross plate (1) and is slidably connected to the cross plate (1); the bottom of the vertical rod (3) extends to the bottom of the rectangular tube (12); Each of the poles (3) has a horizontal plate (31) installed on its top; a protective ring (32) is fixed to the outer ring of multiple horizontal plates (31), and the rotation range of the propeller on the UAV is located in the inner ring of the protective ring (32) and does not contact the protective ring (32).

3. The UAV landing buffer device according to claim 2, characterized in that: The bottom of the protective ring (32) is fixedly equipped with evenly distributed protective rods (33).

4. The UAV landing buffer device according to claim 1, characterized in that: The upright (3) extends to one side above the cross plate (1) and a limiting ring (34) is fixed thereon; the top of the limiting ring (34) is provided with threads on the upright (3); The horizontal plate (31) has a circular groove (24), and the circular groove (24) on the horizontal plate (31) is fitted onto the upright (3) above the limiting ring (34); a nut (35) is provided above each circular groove (24), and the nut (35) is used to lock the horizontal plate (31).

5. The UAV landing buffer device according to claim 4, characterized in that: The bottom of the rectangular tube (12) is provided with a cover (4), and the cover (4) is fixed to the rectangular tube (12) by bolts; The top of the cover (4) is provided with a groove (41), and the upright (3) rotates in the groove (41); The cover (4) is located on the base plate (13) and is fixed to the base plate (13) by bolts.

6. The UAV landing buffer device according to claim 1, characterized in that: A rectangular block (42) slides inside the rectangular tube (12); The rectangular block (42) has a threaded groove in the middle, and the upright (3) passes through the threaded groove and rotates in the groove (41); the spring in the rectangular tube (12) is located above the rectangular block (42); The bottom of the upright (3) is threaded, and the thread engages with the threaded groove.

7. The UAV landing buffer device according to claim 6, characterized in that: Each of the convex blocks (22) has an extension plate (5) fixed on the side away from the rectangular tube (12); The extension plate (5) extends out from the convex groove (21).

8. The UAV landing buffer device according to claim 7, characterized in that: The two extension plates (5) located on the same side extend out of the convex groove (21) and are connected and fixed by the connecting plate (51).

9. The UAV landing buffer device according to claim 8, characterized in that: Each of the extension plates (5) is provided with a groove (52); An adjusting plate (53) slides within the groove (52); the adjusting plate (53) is provided with a spring, and the other side of the spring is fixed within the groove (52).

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