Unmanned aerial vehicle undercarriage

Abstract

The invention belongs to the technical field of telescopic undercarriages, and particularly relates to an unmanned aerial vehicle undercarriage which comprises a mounting part, a connecting mechanism, a supporting mechanism, an adjusting mechanism, a control mechanism and a buffering mechanism. The mounting part comprises a fixing frame and a mounting plate connected with an unmanned aerial vehicle body; the connecting mechanism comprises a sliding frame and a fixing strip, the fixing strip is fixedly installed on the bottom face of the fixing frame, and the sliding frame is elastically arranged on the side wall of the fixing strip. The supporting mechanism comprises a mounting cylinder and a supporting rod, the sliding frame penetrates through the mounting cylinder and is rotationally connected with the mounting cylinder, and the outer wall of the supporting rod is connected with the outer wall of the mounting cylinder through an elastic strip; the adjusting mechanism comprises a transmission shaft and a jacking plate, the transmission shaft is fixedly installed on the upper end face of the jacking plate, and the jacking plate is used for jacking the sliding frame; the control mechanism is used for locking and releasing the transmission shaft; the buffer mechanism comprises a control cylinder and a control plug, and the control cylinder is provided with an output end and an input end which are communicated in one direction; the structure is matched with resistance reduction, vibration reduction and stable take-off and landing, and the endurance of the unmanned aerial vehicle is

Description

Technical Field

[0001] This invention belongs to the field of telescopic landing gear technology, specifically a landing gear for unmanned aerial vehicles (UAVs). Background Technology

[0002] With the rapid development of drone technology, its application in many fields such as aerial surveying and mapping, logistics and transportation, power line inspection, and agricultural plant protection is becoming increasingly widespread. As a key load-bearing component of drones, the landing gear is directly related to the take-off and landing safety, flight stability and service life of drones.

[0003] Currently, most drone landing gears on the market adopt a fixed design. This type of landing gear is widely used in small and medium-sized drones due to its simple structure and low manufacturing cost. However, in actual use, it has gradually revealed many technical defects that cannot be ignored.

[0004] During flight, the fixed landing gear remains in the deployed state. Its protruding structure significantly increases air resistance. Increased air resistance not only leads to higher energy consumption and a significantly shortened flight range for drones, but also directly limits their operating radius and mission duration, especially for small drones that rely on battery power.

[0005] During the landing phase, fixed landing gear lacks an effective cushioning and vibration reduction mechanism when it contacts the ground. The impact and vibration from the ground are directly transmitted to the drone body. The drone body integrates a large number of precision electronic components, sensors, and shooting equipment. These components are extremely sensitive to vibration. Long-term vibration transmission can easily lead to loosening of components, poor contact, or even damage to core components, resulting in data loss or equipment failure, and seriously reducing the service life of the drone.

[0006] Therefore, the present invention provides a landing gear for unmanned aerial vehicles (UAVs). Summary of the Invention

[0007] In order to overcome the shortcomings of the prior art, at least one technical problem raised in the background art is solved.

[0008] The technical solution adopted by the present invention to solve its technical problem is: a UAV landing gear according to the present invention, comprising an installation part, a connecting mechanism, a supporting mechanism, an adjusting mechanism, a control mechanism and a buffer mechanism;

[0009] The mounting section includes a mounting bracket and a mounting plate that connects to the drone body;

[0010] The connecting mechanism includes a sliding frame and a fixing bar. The fixing bar is fixedly installed on the bottom surface of the fixing frame, and the sliding frame is elastically set on the side wall of the fixing bar.

[0011] The support mechanism includes a mounting cylinder and a support rod. The sliding frame passes through the mounting cylinder and is rotatably connected to the mounting cylinder. The outer wall of the support rod is connected to the outer wall of the mounting cylinder by an elastic strip.

[0012] The adjustment mechanism includes a drive shaft and a top pressure plate. The drive shaft is fixedly installed on the upper end face of the top pressure plate, and the top pressure plate is used to press down on the sliding frame.

[0013] The control mechanism is used to lock and release the drive shaft;

[0014] The buffer mechanism includes a control cylinder and a control plug. The control cylinder has a unidirectional output end and an input end. The sliding of the control plug is controlled by the rotation of the mounting cylinder. The outer wall of the control plug slides and fits against the inner wall of the control cylinder.

[0015] Preferably, a guide cylinder is fixedly installed on the upper end face of the fixed frame, an adjusting plate is slidably installed on the inner wall of the guide cylinder, a drive shaft passes through the adjusting plate, a spiral groove is opened on the radial outer wall of the drive shaft, and a ball bearing that slides with the spiral groove is provided on the inner wall of the adjusting plate.

[0016] A connecting rod is fixedly installed on the upper end of the fixing strip, and the other end of the connecting rod is fixedly connected to the bottom surface of the fixing frame.

[0017] Preferably, the control mechanism includes a connecting pin, a limit pin, a controller, and a limit groove formed on the outer wall of the connecting pin;

[0018] One end of the connecting pin is fixedly connected to the outer wall of the adjusting plate, the limiting pin is used to insert into the limiting groove, the controller is fixedly installed on the inner wall of the mounting plate, and the sliding of the limiting pin is controlled by magnetic force.

[0019] Preferably, a sliding plate is elastically installed on the inner wall of the mounting plate, and the outer wall of the sliding plate slides against the inner wall of the mounting plate;

[0020] The side wall of the mounting cylinder is provided with a fan-shaped groove, and a fan-shaped piece is slidably installed on the inner wall of the fan-shaped groove. One end of the fan-shaped piece is fixedly connected to the side wall of the sliding frame.

[0021] Preferably, a guide rod is fixedly installed on the side wall of the fixing strip, the guide rod passes through the sliding frame and is slidably connected to the sliding frame;

[0022] A blocking rod is fixedly installed on the bottom surface of the fixed frame, and a lever is fixedly installed on the outer wall of the mounting cylinder. The blocking rod is used to block the lever.

[0023] A transmission cylinder is fixedly installed on the inner wall of the mounting cylinder. The transmission cylinder is rotatably connected to one side wall of the sliding frame via a torsion spring. The side wall of the sliding frame is provided with a bearing connected to the transmission cylinder.

[0024] Preferably, a transmission disc is slidably mounted on the side wall of the sliding frame, and a control rod is fixedly mounted on the side wall of the transmission disc. One end of the control rod extends into the inner cavity of the control cylinder and is fixedly connected to the outer wall of the control plug.

[0025] A filter cover is fixedly installed on the inner wall of the control cylinder, and the filter cover is located at the output end of the control cylinder.

[0026] Preferably, a control panel is fixedly installed on the inner wall of the mounting cylinder, a control protrusion is fixedly installed on the outer wall of the control panel, and a transmission protrusion is fixedly installed on the outer wall of the transmission disc. The control protrusion is used to press against the transmission protrusion.

[0027] Both the transmission disc and the control disc have connecting rings fixedly installed on their side walls, and the two connecting rings are connected by elastic elements.

[0028] The outer wall of the mounting cylinder has a notch, a reinforcing rod is fixedly installed at the notch, and an elastic plate is fixedly installed on the outer wall of the mounting cylinder to seal the notch.

[0029] The beneficial effects of this invention are as follows:

[0030] 1. This invention effectively solves the core defects of existing fixed landing gear by setting up a sliding frame, support rod, and control cylinder. During takeoff, the sliding frame approaches the fixed bar under the action of the elastic element, causing the support rod to retract and be stored, preventing it from protruding outside the fuselage and interfering with airflow. This significantly reduces air resistance during flight, reduces energy consumption, and greatly improves the UAV's endurance and flight speed, breaking through the bottleneck of the limited endurance of fixed landing gear. During landing, the lubricating oil in the control cylinder flows through a one-way valve to generate a damping effect. On the one hand, it controls the support rod to open and close at a uniform speed, ensuring accurate and synchronous support angles and avoiding fuselage tilting caused by force imbalance. On the other hand, it absorbs the ground reaction force through damping, reducing the transmission of vibration to the fuselage and internal precision components, preventing component loosening, damage, or data loss, and ensuring the safety and stability of the takeoff and landing process.

[0031] 2. This invention further optimizes the landing gear performance by incorporating a controller, sector-shaped plates, and guide rods. The controller, in conjunction with limit pins, enables automatic locking and releasing of the support rod's retraction and extension states via the UAV's MCU, eliminating the need for manual intervention and improving operational convenience and control precision. The cooperation between the sector-shaped plates and sector-shaped grooves strictly limits the maximum deflection angle of the support rod, preventing excessive deflection from affecting the support effect. Simultaneously, the guide rod provides stable guidance for the sliding frame, reducing offset and wear during sliding and extending the structural lifespan. Furthermore, this design minimizes the space occupied by the landing gear in the retracted state, avoiding interference with other components and adapting to more complex flight scenarios. Moreover, the coordinated operation of the structures ensures stable force distribution during landing on various terrains, further expanding the application range of UAVs. Attached Figure Description

[0032] The invention will now be further described with reference to the accompanying drawings.

[0033] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0034] Figure 2 This is a schematic diagram of the installation of the guide cylinder in this invention;

[0035] Figure 3 This is a schematic diagram of the blocking rod in this invention;

[0036] Figure 4 This is a schematic diagram of the installation of the limit pin in this invention;

[0037] Figure 5 This is a schematic diagram of the installation of the adjustment disc in this invention;

[0038] Figure 6 This is a schematic diagram of the installation of the mounting cylinder in this invention;

[0039] Figure 7 This is a schematic diagram of the installation of the transmission disc in this invention;

[0040] Figure 8 This is a schematic diagram of the installation of the control bump in this invention;

[0041] Figure 9 This is a schematic diagram of the installation of the filter cover in this invention.

[0042] In the diagram: 1. Fixed frame; 2. Mounting plate; 3. Blocking rod; 4. Guide cylinder; 5. Top pressure plate; 6. Support rod; 7. Sliding frame; 8. Mounting cylinder; 9. Sector groove; 10. Guide rod; 11. Paddle plate; 12. Fixed strip; 13. Connecting rod; 14. Elastic sheet; 15. Sector sheet; 16. Drive shaft; 17. Spiral groove; 18. Controller; 19. Sliding plate; 20. Limit pin; 21. Limit groove; 22. Connecting pin; 23. Adjusting disc; 24. Transmission protrusion; 25. Control disc; 26. Transmission disc; 27. Transmission cylinder; 28. Bearing; 29. ​​Control cylinder; 30. Reinforcing rod; 31. Control rod; 32. Control protrusion; 33. Connecting ring; 34. Filter cover; 35. Control plug. Detailed Implementation

[0043] 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.

[0044] like Figures 1 to 9 As shown, the UAV landing gear of the present invention includes an installation part, a connecting mechanism, a supporting mechanism, an adjusting mechanism, a control mechanism, and a buffer mechanism.

[0045] The mounting section includes a mounting bracket 1 and a mounting plate 2 that connects to the drone body. The mounting plate 2 and the drone body are designed as a single unit. The outer wall of the mounting bracket 1 has through holes for bolts to pass through. In use, the mounting bracket 1 is fixed to the bottom of the drone by bolts.

[0046] The connecting mechanism includes a sliding frame 7 and a fixing bar 12. The fixing bar 12 is fixedly installed on the bottom surface of the fixing frame 1. The sliding frame 7 is elastically disposed on the side wall of the fixing bar 12. A spring is provided on the side wall of the fixing bar 12. The other end of the spring is connected to the sliding frame 7. The elastic force of the spring pulls the sliding frame 7, so that the sliding frame 7 tends to move closer to the fixing bar 12 in real time.

[0047] The support mechanism includes an mounting cylinder 8 and a support rod 6. A sliding frame 7 passes through the mounting cylinder 8 and is rotatably connected to the mounting cylinder 8. The outer wall of the support rod 6 is connected to the outer wall of the mounting cylinder 8 by an elastic strip. The elastic strip is made of elastic copper plate. An anti-slip rubber sleeve is fitted on the outer wall of the support plate 6.

[0048] When the drone lands, the sliding adjustment slide 7 moves away from the fixed bar 12. During this process, the mounting cylinder 8 is rotated to open the support rod 6. Upon landing, the support rod 6 contacts the ground to provide support. During the drone's takeoff, the slide 7 slides toward the fixed bar 12, and then the mounting cylinder 8 is rotated to retract the support rod 6.

[0049] When the drone lands, the support rod 6 extends to provide support. The anti-slip rubber sleeve increases friction with the ground, preventing the drone from directly contacting the ground and causing collision damage. It also ensures stability upon landing and prevents equipment failure caused by sideslip. After takeoff, the support rod 6 retracts, which can significantly reduce air resistance during flight, improve the drone's flight speed and endurance, and prevent the support rod in the extended state from interfering with airflow.

[0050] The adjustment mechanism includes a drive shaft 16 and a top pressure plate 5. The drive shaft 16 is fixedly installed on the upper end face of the top pressure plate 5. The top pressure plate 5 is used to press the sliding frame 7. The top pressure plate 5 is a cam, and its outer wall slides against the outer wall of the sliding frame 7. When the drive shaft 16 is rotated, it drives the top pressure plate 5 to rotate, which, in conjunction with the elastic force on the sliding frame 7, controls the sliding of the sliding frame 7.

[0051] The control mechanism is used to lock and release the drive shaft 16. During the takeoff of the UAV, the support rod 6 is adjusted to retract, at which time the drive shaft 16 is locked, keeping the support rod 6 in a retracted state. When the UAV lands and approaches the ground, the drive shaft 16 is released, causing the sliding frame 7 to slide and the mounting cylinder 8 to deflect, thereby causing the support rod 6 to deflect and achieve the release effect.

[0052] The buffer mechanism includes a control cylinder 29 and a control plug 35. The control cylinder 29 has a unidirectional output end and an input end. Both the output end and the input end of the control cylinder 29 are equipped with a one-way valve, and the two one-way valves have opposite conduction directions.

[0053] The sliding of the control plug 35 is controlled by the rotation of the mounting cylinder 8. The outer wall of the control plug 35 slides and fits against the inner wall of the control cylinder 29. The inner cavity of the mounting cylinder 8 is filled with lubricating oil. When the control plug 35 slides back and forth, the lubricating oil enters the control cylinder 29 through the input end and is discharged from the output end.

[0054] When the lubricating oil passes through the output and input ends of the control cylinder 29, a damping effect is generated, thereby controlling the mounting cylinder 8 to rotate at a uniform speed. During the descent of the UAV, the support rod 6 is kept to open at a uniform speed and stably. At the same time, during the contact of the support rod 6 with the ground, the damping effect plays a role in shock absorption.

[0055] Damped, uniform opening without instantaneous impact force avoids the transmission of impact loads generated by elastic acceleration to the fuselage, preventing unstable attitudes such as vertical swaying and horizontal shaking due to impact. This ensures that the UAV approaches the ground and lands smoothly, reducing the risk of attitude loss of control. Compared to the support angle deviation that may occur with elastic acceleration, damped, uniform opening allows the support rod 6 to maintain the preset support attitude at all times, avoiding fuselage tilting caused by angle deviation. This ensures that the support surface is in stable contact with the ground, allowing the UAV to maintain a stable force attitude throughout the descent, reducing landing failures caused by attitude abnormalities. At the same time, it avoids the instantaneous impact force generated by rapid opening from causing mechanical wear to the mounting cylinder 8, sliding frame 7, and other connecting structures, extending the structural stability and service life of the landing gear. It also allows operators to clearly predict the support status, improving the controllability of the landing operation.

[0056] The cushioning effect of support rod 6 when it contacts the ground can effectively absorb the ground reaction force through the damping effect, reduce the transmission of landing vibration to the drone body and internal precision components (such as sensors, batteries, shooting equipment, etc.), avoid the loosening of components, data loss or damage to core components caused by vibration, reduce the direct damage of ground impact to the body, and ensure the safety, stability and long-term reliability of the drone during take-off and landing.

[0057] A guide cylinder 4 is fixedly installed on the upper end face of the fixed frame 1. An adjusting plate 23 is slidably installed on the inner wall of the guide cylinder 4. A sliding groove is provided on the inner wall of the guide cylinder 4 for the adjusting plate 23 to slide, so as to prevent the adjusting plate 23 from deflecting. A spring is installed on the bottom surface of the adjusting plate 23, and the other end of the spring is connected to the inner wall of the guide cylinder 4, so that the adjusting plate 23 has a downward sliding tendency in real time.

[0058] The drive shaft 16 passes through the adjusting plate 23. The radial outer wall of the drive shaft 16 is provided with a spiral groove 17. The inner wall of the adjusting plate 23 is provided with balls that slide in cooperation with the spiral groove 17. The sliding adjusting plate 23 drives the drive shaft 16 to rotate through the cooperation of the balls and the spiral groove 17, which in turn drives the top pressure plate 5 to rotate.

[0059] When the drone is in flight, the sliding adjustment disk 23 is moved to its highest position, at which time the support rod 6 retracts. When the drone lands, the control adjustment disk 23 is lowered, which drives the transmission shaft 16 to rotate, thereby causing the support rod 6 to open.

[0060] A connecting rod 13 is fixedly installed on the upper end face of the fixing strip 12. The other end of the connecting rod 13 is fixedly connected to the bottom surface of the fixing frame 1. The connection between the fixing strip 12 and the fixing frame 1 is achieved through the connecting rod 13. The side wall of the top pressure plate 5 is provided with a groove for the connecting rod 13 to enter.

[0061] In a preferred embodiment of the present invention, the control mechanism includes a connecting pin 22, a limiting pin 20, a controller 18, and a limiting groove 21 formed on the outer wall of the connecting pin 22. The controller 18 is a common electromagnet, which is controlled by the MCU built into the UAV.

[0062] One end of the connecting pin 22 is fixedly connected to the outer wall of the adjusting plate 23. The limiting pin 20 is used to insert into the limiting groove 21. The controller 18 is fixedly installed on the inner wall of the mounting plate 2 and controls the sliding of the limiting pin 20 by magnetic force. When the limiting pin 20 is inserted into the limiting groove 21, the adjusting plate 23 is fixed.

[0063] When the fixed frame 1 is assembled with the drone, the guide cylinder 4 is inserted into the mounting plate 2, and then the sliding connecting pin 22 slides out of the guide cylinder 4 until the limit pin 20 is inserted into the limit groove 21, thereby fixing the adjustment plate 23. At this time, the support rod 6 remains in a retracted state. When the drone lands, the MCU of the drone sends a command to the controller 18 (causing the controller 18 to be energized and generate magnetic force) to attract the limit pin 20, causing the limit pin 20 to separate from the limit groove 21. At this time, the adjustment plate 23 is subjected to elastic sliding, which drives the transmission shaft 16 to rotate until the support rod 6 deflects and unfolds, so as to provide support during landing.

[0064] A sliding plate 19 is elastically installed on the inner wall of the mounting plate 2. The outer wall of the sliding plate 19 slides against the inner wall of the mounting plate 2. The outer wall of the sliding plate 19 is fixedly connected to the outer wall of the limiting pin 20 to improve the stability of the sliding of the limiting pin 20.

[0065] The side wall of the mounting cylinder 8 is provided with a fan-shaped groove 9, and a fan-shaped piece 15 is slidably installed on the inner wall of the fan-shaped groove 9. One end of the fan-shaped piece 15 is fixedly connected to the side wall of the sliding frame 7. Through the cooperation of the fan-shaped piece 15 and the fan-shaped groove 9, the maximum deflection angle of the mounting cylinder 8 is limited to prevent the support rod 6 from deflecting excessively when the UAV lands.

[0066] In a preferred embodiment of the present invention, a guide rod 10 is fixedly installed on the side wall of the fixing strip 12. The guide rod 10 passes through the sliding frame 7 and is slidably connected to the sliding frame 7. At least two guide rods 10 are provided. The stability of the sliding frame 7 is improved by providing guide rods 10.

[0067] A blocking rod 3 is fixedly installed on the bottom surface of the fixed frame 1, and a lever 11 is fixedly installed on the outer wall of the mounting cylinder 8. The blocking rod 3 is used to block the lever 11. When the sliding frame 7 slides toward the fixed bar 12, the lever 11 is blocked by the blocking rod 3, which drives the mounting cylinder 8 to rotate so as to facilitate the retraction of the support rod 6. As the sliding frame 7 slides, the lever 11 slides on the bottom surface of the blocking rod 3. At this time, the support rod 6 remains in a retracted state.

[0068] A transmission cylinder 27 is fixedly installed on the inner wall of the mounting cylinder 8. The transmission cylinder 27 is rotatably connected to one side wall of the sliding frame 7 via a torsion spring. The side wall of the sliding frame 7 is provided with a bearing 28 connected to the transmission cylinder 27. The stability of the rotation of the mounting cylinder 8 is improved by setting the bearing 28.

[0069] When the drone lands, the top pressure plate 5 rotates and pushes the sliding frame 7 to slide. At this time, the deflector 11 slides along the bottom surface of the blocking rod 3. In this state, the support rod 6 remains in a retracted state until the deflector 11 moves to the end of the blocking rod 3. At this time, the mounting cylinder 8 is deflected by the torsion spring force until the support rod 6 opens. When the mounting cylinder 8 rotates, the damping effect intervenes again, which can effectively reduce the time for the support rod 6 to move to the support position.

[0070] A transmission disc 26 is slidably mounted on the side wall of the sliding frame 7. A control rod 31 is fixedly mounted on the side wall of the transmission disc 26. The sliding transmission disc 26 drives the control rod 31 to slide. One end of the control rod 31 extends into the inner cavity of the control cylinder 29 and is fixedly connected to the outer wall of the control plug 35. The sliding of the control plug 35 drives the lubricating oil sliding frame 7.

[0071] A filter cover 34 is fixedly installed on the inner wall of the control cylinder 29. The filter cover 34 is located at the output end of the control cylinder 29. By setting the filter cover 34, the sludge inside the lubricating oil inside the mounting cylinder 8 is blocked and collected in the inner cavity of the control cylinder 29 to maintain the lubrication effect.

[0072] A control disc 25 is fixedly installed on the inner wall of the mounting cylinder 8, and a control protrusion 32 is fixedly installed on the outer wall of the control disc 25. When the mounting cylinder 8 rotates, it drives the control disc 25 and the control protrusion 32 to rotate.

[0073] A transmission protrusion 24 is fixedly installed on the outer wall of the transmission disc 26. The control protrusion 32 is used to press the transmission protrusion 24, so that when the mounting cylinder 8 rotates, the control protrusion 32 drives the transmission protrusion 24 to press the transmission protrusion 24, which drives the control plug 35 to slide, controls the flow of lubricating oil to collect slag, and generates a damping effect.

[0074] Both the transmission disc 26 and the control disc 25 have connecting rings 33 fixedly installed on their side walls. The two connecting rings 33 are connected by elastic elements. The elastic force of the elastic elements makes the control disc 25 and the transmission disc 26 tend to move closer to each other in real time. The connecting rings 33 are designed to accommodate the rotation of the control disc 25.

[0075] The outer wall of the mounting cylinder 8 has a notch, and a reinforcing rod 30 is fixedly installed at the notch. An elastic sheet 14 is fixedly installed on the outer wall of the mounting cylinder 8. The elastic sheet 14 is used to close the notch on the outer wall of the mounting cylinder 8. The elastic sheet 14 is a common rubber sheet used to adapt to the pressure change of the lubricating oil inside the mounting cylinder 8 when the transmission disc 26 slides.

[0076] The terms "front," "back," "left," "right," "top," and "bottom" all refer to the figures in the accompanying drawings. Figure 1 Based on the perspective of the observer, the side of the device facing the observer is defined as the front, the left side of the observer is defined as the left, and so on.

[0077] In the description of this invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not 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 this invention.

[0078] 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 landing gear for an unmanned aerial vehicle (UAV), characterized in that: It includes an installation section, a connection mechanism, a support mechanism, an adjustment mechanism, a control mechanism, and a buffer mechanism; The mounting section includes a fixing frame (1) and a mounting plate (2) that is connected to the drone body. The connecting mechanism includes a sliding frame (7) and a fixing strip (12). The fixing strip (12) is fixedly installed on the bottom surface of the fixing frame (1), and the sliding frame (7) is elastically arranged on the side wall of the fixing strip (12). The support mechanism includes an installation cylinder (8) and a support rod (6). The sliding frame (7) passes through the installation cylinder (8) and is rotatably connected to the installation cylinder (8). The outer wall of the support rod (6) is connected to the outer wall of the installation cylinder (8) by an elastic strip. The adjustment mechanism includes a drive shaft (16) and a top pressure plate (5). The drive shaft (16) is fixedly installed on the upper end face of the top pressure plate (5). The top pressure plate (5) is used to press down on the sliding frame (7). The control mechanism is used to lock and release the drive shaft (16). The buffer mechanism includes a control cylinder (29) and a control plug (35). The control cylinder (29) has a unidirectional output end and an input end. The sliding of the control plug (35) is controlled by the rotation of the mounting cylinder (8). The outer wall of the control plug (35) slides against the inner wall of the control cylinder (29).

2. The unmanned aerial vehicle landing gear according to claim 1, characterized in that: A guide cylinder (4) is fixedly installed on the upper end face of the fixed frame (1). An adjusting disc (23) is slidably installed on the inner wall of the guide cylinder (4). The transmission shaft (16) passes through the adjusting disc (23). A spiral groove (17) is opened on the radial outer wall of the transmission shaft (16). A ball bearing that slides with the spiral groove (17) is provided on the inner wall of the adjusting disc (23). A connecting rod (13) is fixedly installed on the upper end face of the fixing strip (12), and the other end of the connecting rod (13) is fixedly connected to the bottom surface of the fixing frame (1).

3. The unmanned aerial vehicle landing gear according to claim 2, characterized in that: The control mechanism includes a connecting pin (22), a limiting pin (20), a controller (18), and a limiting groove (21) formed on the outer wall of the connecting pin (22). One end of the connecting pin (22) is fixedly connected to the outer wall of the adjusting plate (23), the limiting pin (20) is used to be inserted into the limiting groove (21), and the controller (18) is fixedly installed on the inner wall of the mounting plate (2) and the limiting pin (20) is controlled to slide by magnetic force.

4. The unmanned aerial vehicle landing gear according to claim 3, characterized in that: The inner wall of the mounting plate (2) is elastically fitted with a sliding plate (19), the outer wall of the sliding plate (19) is slidably attached to the inner wall of the mounting plate (2), and the outer wall of the sliding plate (19) is fixedly connected to the outer wall of the limiting pin (20). The side wall of the mounting cylinder (8) is provided with a fan-shaped groove (9), and a fan-shaped piece (15) is slidably installed on the inner wall of the fan-shaped groove (9). One end of the fan-shaped piece (15) is fixedly connected to the side wall of the sliding frame (7).

5. The unmanned aerial vehicle landing gear according to claim 4, characterized in that: A guide rod (10) is fixedly installed on the side wall of the fixing strip (12). The guide rod (10) passes through the sliding frame (7) and is slidably connected to the sliding frame (7). A blocking rod (3) is fixedly installed on the bottom surface of the fixed frame (1), and a lever (11) is fixedly installed on the outer wall of the mounting cylinder (8). The blocking rod (3) is used to block the lever (11). The inner wall of the mounting cylinder (8) is fixedly installed with a transmission cylinder (27). The transmission cylinder (27) is rotatably connected to one side wall of the sliding frame (7) through a torsion spring. The side wall of the sliding frame (7) is provided with a bearing (28) connected to the transmission cylinder (27).

6. The unmanned aerial vehicle landing gear according to claim 5, characterized in that: A transmission disc (26) is slidably mounted on the side wall of the sliding frame (7), and a control rod (31) is fixedly mounted on the side wall of the transmission disc (26). One end of the control rod (31) extends into the inner cavity of the control cylinder (29) and is fixedly connected to the outer wall of the control plug (35). A filter cover (34) is fixedly installed on the inner wall of the control cylinder (29), and the filter cover (34) is located at the output end of the control cylinder (29).

7. A drone landing gear according to claim 6, characterized in that: The inner wall of the mounting cylinder (8) is fixedly mounted with a control disc (25), the outer wall of the control disc (25) is fixedly mounted with a control protrusion (32), the outer wall of the transmission disc (26) is fixedly mounted with a transmission protrusion (24), and the control protrusion (32) is used to press against the transmission protrusion (24). Both the transmission disc (26) and the control disc (25) are fixedly mounted with connecting rings (33), and the two connecting rings (33) are connected by elastic elements. The outer wall of the mounting cylinder (8) has a notch, and a reinforcing rod (30) is fixedly installed at the notch of the outer wall of the mounting cylinder (8). An elastic sheet (14) is fixedly installed on the outer wall of the mounting cylinder (8). The elastic sheet (14) is used to close the notch of the outer wall of the mounting cylinder (8).

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