Landing shock absorbing frame and unmanned aerial vehicle

Abstract

The application discloses a landing shock-absorbing frame, which comprises a landing shock-absorbing frame assembly, shock-absorbing containing boxes, a driving mechanism and a central control system. The landing shock-absorbing frame assembly is used for providing supporting force for shock-absorbing and buffering during landing and comprises symmetrically arranged supporting cross bars and supporting inclined vertical rods respectively installed on top surfaces of the supporting cross bars. The bottom of each shock-absorbing containing box is in the shape of an open port and is fixed to the bottom surface of each supporting cross bar. One of the shock-absorbing containing boxes is provided with a shock-absorbing air bag wound up, and the free end of the shock-absorbing air bag is connected with a pull rope which extends into the other shock-absorbing containing box. The driving mechanism is arranged in the two shock-absorbing containing boxes and is used for expanding and unfolding and winding up the shock-absorbing air bag. The central control system comprises a PLC module, a landing environment monitoring module and a landing communication module. The application can adapt to various complex landing scenes and improve the shock-absorbing effect.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle technology, and in particular to a landing shock absorber and an unmanned aerial vehicle. Background Technology

[0002] With the development of drone technology, unmanned aerial vehicles (UAVs) have been widely used in various fields such as military, civilian, and scientific research. However, in the actual use of UAVs, especially during takeoff and landing, they face many challenges. Various adverse factors may be encountered during takeoff and landing, such as varying ground hardness, wind speed changes, and extreme temperatures. These factors can all impact the aircraft, affecting its stability and safety.

[0003] Currently, most unmanned aerial vehicle (UAV) takeoff and landing vibration damping systems on the market have the following shortcomings: Most damping systems use a single damping method, such as simple springs or rubber pads, which cannot cope with the complex and ever-changing takeoff and landing environment. This single damping method is difficult to provide sufficient cushioning effect, especially in extreme environments, where the damping effect is limited. Summary of the Invention

[0004] The purpose of this invention is to provide a landing damping frame and an unmanned aerial vehicle to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a landing damping frame, comprising: a landing damping frame assembly, a damping housing, a drive mechanism, and a central control system.

[0006] The landing damper assembly provides shock absorption and cushioning support during takeoff and landing and includes symmetrically arranged support crossbars and support inclined uprights respectively installed on the top surface of the support crossbars;

[0007] The bottom of the vibration damping housing is open and fixed to the bottom surface of each support crossbar. One of the vibration damping housings has a rolled-up vibration damping airbag. The free end of the vibration damping airbag is connected to a pull rope, which extends to another vibration damping housing.

[0008] The drive mechanism is located in two vibration-damping housings and is used for the expansion, unfolding, and retraction of the vibration-damping airbags;

[0009] The central control system includes a PLC module, a landing environment monitoring module, and a landing communication module.

[0010] In this preferred embodiment, the landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit, and a landing wind speed monitoring unit, and the communication module includes a Wi-Fi network unit.

[0011] In a preferred embodiment of this solution, the landing support point attribute recognition unit includes a recognition camera, which identifies whether the landing support point is loose or hard.

[0012] The take-off and landing temperature monitoring unit includes a temperature sensor, which monitors the temperature at the take-off and landing point and transmits the data to the PLC module through a communication module.

[0013] The take-off and landing wind speed monitoring unit includes a wind speed sensor, which monitors the wind speed at the take-off and landing point and transmits the data to the PLC module through a communication module.

[0014] In a preferred embodiment, the driving mechanism includes a winding shaft rotatably mounted in each vibration damping housing and a micro motor mounted on the outer wall of the diagonally intersecting ends of the two vibration damping housings.

[0015] In a preferred embodiment of this scheme, the ends of the two vibration damping housings are further equipped with multi-directional anti-tilt vibration damping components. The multi-directional anti-tilt vibration damping components include anti-tilt vibration damping components for lifting and lowering that are respectively installed at the bottom of both ends of each vibration damping housing, and anti-tilt vibration damping components for lifting and lowering that are symmetrically installed on the lower part of the opposite side of the two vibration damping housings.

[0016] In this preferred embodiment, the ends of the two landing-side anti-tilt damping components that are furthest from the damping housing are tilted upwards, so that the back of the landing-side anti-tilt damping component has an arc-shaped curved surface structure.

[0017] In this preferred embodiment, each of the anti-tilt and anti-roll vibration damping components before and after takeoff and landing is provided with a wave-damping part at the end near the vibration damping housing, and the end of each anti-tilt and anti-roll vibration damping component before and after takeoff and landing is provided with an arc-shaped upturned end.

[0018] In this preferred embodiment, each of the vibration damping housings has a rubber vibration damping base frame bonded to its bottom surface. When the housing is raised or lowered, the rubber vibration damping base frame can provide basic buffering and vibration damping. The two rubber vibration damping base frames have symmetrical holes on opposite sides for the pull rope to pass through.

[0019] In this preferred embodiment, each of the supporting inclined uprights is connected to a hydraulic damping rod at its top. The hydraulic damping rod is covered by a U-shaped mounting plate, and a second air spring is installed on the inner walls of both sides of the U-shaped mounting plate. The two second air springs are fixedly connected to the outer wall of the hydraulic damping rod at opposite ends.

[0020] An unmanned aerial vehicle (UAV) includes a base box, a top cover mounted on the top of the base box, and a landing shock absorber mounted on the bottom of the base box.

[0021] Compared with the prior art, the technical effects and advantages of the present invention are as follows:

[0022] The landing gear and unmanned aerial vehicle form a comprehensive vibration reduction system through various vibration reduction structures, including vibration reduction airbags, hydraulic damping rods, rubber vibration reduction base frames, anti-tilt vibration damping components before and after takeoff and landing, and anti-tilt vibration damping components on the sides of the landing area. This system can effectively absorb impact forces from all directions and improve the vibration reduction effect.

[0023] By monitoring the takeoff and landing environment in real time through temperature sensors, wind speed sensors, and recognition cameras, the central control system can automatically adjust the vibration reduction strategy according to different environmental conditions. This intelligent control method makes the vibration reduction system more flexible and adaptable to various complex takeoff and landing scenarios. The PLC module makes precise decisions based on sensor data, controlling the drive mechanism to deploy or retract the vibration-damping airbags to ensure maximum vibration reduction effect.

[0024] The design of the anti-roll dampers before and after takeoff and landing, as well as the anti-roll dampers on the sides, effectively prevents the aircraft from tilting forward, backward, or rolling over during takeoff and landing, thus improving overall stability. The anti-roll dampers before and after takeoff and landing are designed with curved, upward-curving ends and wave-shaped damping sections, providing stability and vibration reduction in the forward and backward directions during takeoff and landing. Attached Figure Description

[0025] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure of the present invention;

[0027] Figure 2 This is a schematic diagram of the mounting structure of the bottom box of the present invention;

[0028] Figure 3 This is a schematic diagram of the structure of the multi-directional anti-tilt vibration damping component of the present invention;

[0029] Figure 4 This is a schematic diagram of the structure of the vibration damping housing of the present invention;

[0030] Figure 5 For the present invention Figure 1 Enlarged structural diagram at point A;

[0031] Figure 6 For the present invention Figure 1 Enlarged structural diagram at point B;

[0032] Figure 7 This is a schematic diagram of the installation structure of the wind speed sensor of the present invention;

[0033] Figure 8 This is a schematic diagram of the mounting structure of the second air spring of the present invention;

[0034] Figure 9 This is a block diagram of the electrical connection of the central control system of the present invention.

[0035] Explanation of reference numerals in the attached figures:

[0036] In the diagram: 1. Landing damping frame assembly; 2. Support crossbar; 3. Support tilting upright; 4. Damping housing box; 5. Pull rope; 6. Rubber damping base frame; 7. Drive mechanism; 8. Damping airbag; 9. Base box; 10. Top cover; 11. Temperature sensor; 12. Rotor component; 13. Hydraulic damping rod; 14. Anti-tilt damping component before and after landing; 15. Arc-shaped upturned end; 16. Wave-shaped damping section; 17. Anti-tilt damping component on the landing side; 18. Multi-directional anti-tilt damping assembly; 19. Rewind shaft; 20. Bearing; 21. Micro motor; 22. Rope threading hole; 23. Identification camera; 24. Mounting upper plate; 25. First air spring; 26. Mounting lower plate; 27. Rubber damping sleeve; 28. U-shaped mounting plate; 29. ​​Second air spring; 30. Pump body component; 31. Wind speed sensor. Detailed Implementation

[0037] In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without one or more of these details. In other instances, certain technical features well-known in the art have not been described in order to avoid obscuring the invention.

[0038] Unless otherwise defined, the directions mentioned herein, such as up, down, left, right, front, back, inside, and outside, are based on the directions shown in the figures of this invention, and are explained here together.

[0039] This embodiment provides, for example Figures 1 to 9 The landing damper shown includes: a landing damper assembly 1, a damping housing 4, a drive mechanism 7, and a central control system.

[0040] In this embodiment, the landing and vibration damping frame assembly 1 is used to provide shock absorption and buffering support during landing and includes symmetrically arranged support crossbars 2 and support inclined uprights 3 respectively installed on the top surface of the support crossbars 2; the support inclined uprights 3 serve as a vertical support structure, connecting the support crossbars 2 and the vibration damping housing 4, and providing the necessary vertical vibration damping effect during landing.

[0041] In this embodiment, the bottom of the vibration damping housing 4 is open and fixed to the bottom surface of each supporting crossbar 2. One of the vibration damping housing 4 contains a rolled-up vibration damping airbag 8. The free end of the vibration damping airbag 8 is connected to a pull rope 5, which extends into the other vibration damping housing 4. The vibration damping housing 4 serves as a carrier for the vibration damping airbag 8 and other mechanical components, protecting the internal components from external environmental influences and providing an installation position for the drive mechanism 7. The vibration damping airbag 8 provides additional vibration damping effect by inflating, absorbing more impact energy during takeoff and landing and reducing fuselage vibration.

[0042] In this embodiment, the drive mechanism 7 is disposed in the two vibration damping housing boxes 4 and is used for the expansion and contraction of the vibration damping airbag 8.

[0043] In this embodiment, the central control system includes a PLC module, a landing environment monitoring module, and a landing communication module. When the landing environment monitoring module detects that the shock-absorbing airbag 8 needs to be inflated and deployed during landing, the landing environment monitoring module sends a signal to the PLC module through the landing communication module. After receiving the signal, the PLC module controls the drive mechanism 7 to inflate and deploy the shock-absorbing airbag 8 to support and cushion the two housing boxes, so that the shock-absorbing airbag 8 elastically cushions the landing.

[0044] In this embodiment, the landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit, and a landing wind speed monitoring unit, and the communication module includes a Wi-Fi network unit.

[0045] In this embodiment, the landing support point attribute recognition unit includes a recognition camera 23, which recognizes whether the landing support point is loose or hard.

[0046] In this embodiment, the take-off and landing temperature monitoring unit includes a temperature sensor 11, which monitors the temperature at the take-off and landing point and transmits the data to the PLC module through the communication module.

[0047] In this embodiment, the take-off and landing wind speed monitoring unit includes a wind speed sensor 31, which monitors the wind speed at the take-off and landing point and transmits the data to the PLC module through the communication module. When the recognition camera 23 identifies whether the landing support point is loose soil or concrete, it sends the recognition result data to the PLC module via the Wi-Fi network unit. When the PLC module determines that it is hard concrete, it synchronously controls the pump body component 30 and the two micro motors 21 to open, causing the two micro motors 21 to deploy the shock-absorbing airbags 8. The pump body component 30 inflates the shock-absorbing airbags 8, allowing the landing shock-absorbing frame assembly 1 to be buffered and damped during landing by the expanded shock-absorbing airbags 8, the hydraulic damping rods 13, and the second air spring 29. When the recognition camera 23 identifies the landing support point as loose soil, it sends the recognition result data to the PLC module via the Wi-Fi network unit. When the PLC module determines that it is hard concrete, it does not open the micro motors 21 and the pump body component 30. Instead, it shuts down and directly uses the anti-tilt shock absorbers 14 and 17 on the landing side and the rubber shock-absorbing base frame 6 for vibration damping. When temperature sensor 11 detects extreme high or low temperatures, and wind speed sensor 31 detects extreme wind, the detected data is sent to the PLC module via the Wi-Fi network unit. The PLC module synchronously controls the opening of pump body component 30 and two micro motors 21, causing the two micro motors 21 to deploy the shock-absorbing airbags 8. Pump body component 30 inflates and expands the shock-absorbing airbags 8, allowing the landing and vibration damping frame assembly 1 to be buffered and damped during takeoff and landing through the expanded shock-absorbing airbags 8, hydraulic damping rods 13, and second air springs 29. When there are no extreme high or low temperatures or extreme wind, the PLC module is turned off, and vibration is directly damped by the anti-tilt damping components 14 before and after takeoff and landing, the anti-tilt damping components 17 on the side of takeoff and landing, and the rubber damping base frame 6. Pump body component 30 includes an inflation pump and a vacuum pump, used to control the inflation and deflation of the shock-absorbing airbags 8 to achieve their deployment and retraction.

[0048] In this embodiment, the drive mechanism 7 includes a winding shaft 19 rotatably mounted in each vibration damping housing 4 and a micro motor 21 mounted on the outer wall of the diagonally intersecting ends of the two vibration damping housings 4. When it is necessary to unfold the vibration damping airbag 8, one of the micro motors 21 rotates in the opposite direction to release the vibration damping airbag 8 wound by the winding shaft 19, while the other micro motor 21 rotates in the forward direction to pull the vibration damping airbag 8 through the pull rope 5, thereby completing the unfolding of the vibration damping airbag 8. Conversely, the other motor rotates in the opposite direction to complete the winding of the vibration damping airbag 8. Both ends of the two winding shafts 19 are connected to the vibration damping housing 4 through bearings 20. The vibration damping housing 4 used for winding the vibration damping airbag 8 has a pump body component 30 in its inner cavity. The pump body component 30 includes an inflation pump for inflating and unfolding the vibration damping airbag 8 and a vacuum pump for deflating and winding the vibration damping airbag 8.

[0049] In this embodiment, a multi-directional anti-tilt vibration damping assembly 18 is also installed at the ends of the two vibration damping housing boxes 4. The multi-directional anti-tilt vibration damping assembly 18 includes anti-tilt vibration damping components 14 installed at the bottom of both ends of each vibration damping housing box 4 before and after lifting, and anti-tilt vibration damping components 17 symmetrically installed on the lower part of the opposite side of the two vibration damping housing boxes 4 before lifting. Each end of each support crossbar 2 is fitted with a rubber vibration damping sleeve 27, which presses down against the top surface of the vibration damping housing box 4. The vibration damping housing box 4 is connected to the support crossbar 2 by screws. The multi-directional anti-tilt vibration damping assembly 18 combines the functions of multiple anti-tilt vibration damping components, providing an all-round anti-tilt vibration damping effect.

[0050] In this embodiment, the ends of the two anti-tilt dampers 17 on the landing side away from the vibration damping housing 4 are curved upwards, making the back of the anti-tilt damper 17 have an arc-shaped curved surface structure. The anti-tilt damper 17 on the landing side can provide lateral buffering and vibration damping support for the support crossbar 2 and the vibration damping housing 4 during landing.

[0051] In this embodiment, each anti-tilt vibration damper 14 is provided with a wave-shaped vibration damping part 16 at the end near the vibration damping housing 4, and an arc-shaped upward-curved end 15 at the end away from the vibration damping housing 4. When the support crossbar 2 is raised and lowered, the arc-shaped upward-curved end 15 of the anti-tilt vibration damper 14 not only prevents forward or backward tilting, but also provides a buffering and vibration damping effect through the elastic resin material of the anti-tilt vibration damper 14. In addition, the wave-shaped vibration damping part 16 makes line contact with the supporting object at the raising and lowering point during raising and lowering, which can avoid the large vibration amplitude caused by surface contact and the instability of support caused by point contact. The anti-tilt vibration damper 14 is designed with an arc-shaped upward-curved end 15 and a wave-shaped vibration damping part 16 to provide stability and vibration damping function in the forward and backward direction during raising and lowering. The arc-shaped upward-curved end 15 helps to reduce the risk of forward or backward tilting during raising and lowering, thus increasing stability. The wave damping section 16 makes line contact with the ground during takeoff and landing, reducing the amplitude of vibration and enhancing the damping effect. The anti-tilt damping component 17 on the takeoff and landing side provides lateral stability during takeoff and landing, preventing rollover.

[0052] In this embodiment, a rubber vibration damping base frame 6 is bonded to the bottom surface of each vibration damping housing 4. When rising and falling, the rubber vibration damping base frame 6 can provide basic cushioning and vibration reduction. The two rubber vibration damping base frames 6 have symmetrical holes 22 on opposite sides for the pull rope 5 to pass through. The rubber vibration damping base frame 6 is located at the bottom of the vibration damping housing 4, providing initial ground contact cushioning and reducing damage from direct impact.

[0053] In this embodiment, each supporting inclined column 3 is connected to a hydraulic damping rod 13 at its top. A U-shaped mounting plate 28 is provided over the hydraulic damping rod 13, and second air springs 29 are installed on the inner walls of both sides of the U-shaped mounting plate 28. The two second air springs 29 are fixedly connected to the outer wall of the hydraulic damping rod 13 at opposite ends. This provides lateral movement buffering and shock absorption for the hydraulic damping rod 13 and the supporting inclined column 3, while the hydraulic damping rod 13 provides longitudinal buffering and vibration reduction for the supporting inclined column 3. The hydraulic damping rod 13 provides the damping effect required for vibration reduction, absorbing impact energy through fluid flow and reducing the vibration of the machine body. The second air springs 29 provide lateral vibration reduction, working in conjunction with the hydraulic damping rod 13 to improve the overall vibration reduction performance of the system.

[0054] An unmanned aerial vehicle (UAV) includes a base box 9, a top cover 10 mounted on the top of the base box 9, and a landing damping frame mounted on the bottom surface of the base box 9. A hydraulic damping rod 13 of the landing damping frame is hinged to the bottom surface of the base box 9. A U-shaped mounting plate 28 is fixed to the bottom surface of the base box 9. A recognition camera 23 is mounted on the outer wall of the base box 9 in the direction of travel. A temperature sensor 11 and a wind speed sensor 31 are mounted on the top surface of the top cover 10 via a damping connector. The damping connector includes a lower mounting plate 26 embedded inside the top cover 10, a first air spring 25 mounted on the top surface of the lower mounting plate 26, and a top mounting plate 24 mounted on the top of the first air spring 25. The temperature sensor 11 and the wind speed sensor 31 are mounted on the top surface of the top mounting plate 24. The first air spring 25 provides elastic support to assist in the damping effect. Four rotor components 12 are symmetrically mounted on the periphery of the base box 9.

[0055] Working principle:

[0056] The landing gear and unmanned aerial vehicle (UAV) utilize a PLC module to receive and process information from the environmental monitoring module, thereby controlling the actions of the actuators. The landing environmental monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit, and a landing wind speed monitoring unit. The landing communication module, including a Wi-Fi network unit, is responsible for transmitting data between the environmental monitoring module and the PLC module.

[0057] The identification camera 23 captures photos or videos of the landing area and analyzes the images to identify the properties of the support points (such as hard ground or loose soil). Temperature sensor 11 detects the temperature of the landing area, and wind speed sensor 31 detects the wind speed. Temperature sensor 11 and wind speed sensor 31 continuously monitor the temperature and wind speed conditions of the landing area, while the identification camera 23 identifies the properties of the landing support points (such as hard ground or loose soil). The monitored data is transmitted to the PLC module in the central control system via a Wi-Fi network unit. The PLC module receives the data from the landing environment monitoring module and analyzes it. Based on the analysis results, the PLC module determines whether the shock-absorbing airbag 8 needs to be deployed and what shock-absorbing measures to take.

[0058] The system identifies photos or videos of the landing area captured by camera 23. Preprocessing of the acquired images includes scaling, cropping, grayscale conversion, and noise removal to improve image quality for subsequent processing. Image processing algorithms (such as edge detection, texture analysis, and color space conversion) are used to extract useful features from the images. These features can be color distribution, texture patterns, or other features related to ground properties. The extracted features are compared with a known standard feature library to find the most similar features. This standard feature library can be a pre-trained model containing features of different ground types (such as hard ground, grass, and sand). Machine learning algorithms (such as Support Vector Machines (SVM), neural networks, and deep learning) are used to classify the extracted features and determine the ground type. For example, if the feature matching results show that the ground has high hardness and smoothness, the system will identify it as hard ground; if the features show that the ground is relatively soft or uneven, it will be identified as loose soil. The identification results are sent to the PLC module via a Wi-Fi network unit for subsequent vibration reduction strategy decisions.

[0059] If the landing point is concrete (hard ground), the shock-absorbing airbag 8 needs to be deployed. The PLC module controls the micro motor 21 to start, release the shock-absorbing airbag 8 through the winding shaft 19, and unfold it through the pull rope 5. The pump body component 30 starts to inflate the shock-absorbing airbag 8, causing it to expand and provide shock absorption. At the same time, the hydraulic damping rod 13 provides lateral shock absorption through the assistance of the second air spring 29. The hydraulic damping rod 13 itself also provides longitudinal shock absorption by absorbing impact energy through internal fluid movement.

[0060] If the landing site is loose soil, the airbags do not need to be opened. The PLC module controls the micro motor 21 to reverse, and the shock-absorbing airbag 8 is rolled up by the winding shaft 19. The airbag is then evacuated using the vacuum pump inside the pump body component 30. The anti-roll shock absorbers 14 provide shock absorption and support in the front-to-back direction through their wave-shaped shock-absorbing section 16 and the arc-shaped upturned end 15. The arc-shaped curved surface design of the anti-roll shock absorbers 17 on the landing side helps to provide shock absorption on the side and prevent the aircraft from rolling over. The rubber shock-absorbing base frame 6, as the bottom shock absorption device, provides basic cushioning and reduces direct impact during takeoff and landing. The rubber shock-absorbing sleeve 27 is fitted onto the support crossbar 2 to provide additional shock absorption. The hydraulic damping rod 13 provides lateral shock absorption with the assistance of the second air spring 29. The hydraulic damping rod 13 itself also provides longitudinal shock absorption by absorbing impact energy through internal fluid movement.

[0061] The support crossbar 2 and the support tilting upright 3 together form the skeleton of the lifting and lowering shock absorber assembly 1, providing a stable structural support. The shock absorber housing 4 is connected to the support crossbar 2 by screws to ensure a firm connection between the components. The hydraulic damping rod 13 is hinged to the bottom surface of the base box 9. The U-shaped mounting plate 28 is fixed to the bottom surface of the base box 9. The identification camera 23 is installed on the outer wall of the base box 9 in the forward direction. The temperature sensor 11 and the wind speed sensor 31 are installed on the top surface of the upper cover 10 through the shock absorber connector.

[0062] The central control system manages all vibration reduction operations to ensure that the aircraft can land or take off smoothly and safely throughout the entire takeoff and landing process.

[0063] It should be noted that, in this document, relational terms such as "one" and "two" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, the phrase "comprising an element defined as..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0064] 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 vibration damping frame, characterized in that, include: The landing shock absorber assembly (1) provides support force for shock absorption and buffering during landing and includes symmetrically arranged support crossbars (2) and support inclined uprights (3) respectively installed on the top surface of the support crossbars (2). The vibration damping container (4) has an open bottom and is fixed to the bottom surface of each support crossbar (2). One of the vibration damping containers (4) has a rolled-up vibration damping airbag (8). The free end of the vibration damping airbag (8) is connected to a pull rope (5), which extends to the other vibration damping container (4). The drive mechanism (7) is located in the two shock-absorbing housings (4) and is used for the expansion and contraction of the shock-absorbing airbag (8). The drive mechanism (7) includes a winding shaft (19) that is rotatably installed in each shock-absorbing housing (4) and a micro motor (21) installed on the outer wall of the diagonally intersecting ends of the two shock-absorbing housings (4). The central control system includes a PLC module, a landing environment monitoring module, and a landing communication module; The landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit, and a landing wind speed monitoring unit; the communication module includes a Wi-Fi network unit. The landing support point attribute recognition unit includes a recognition camera (23), which recognizes whether the landing support point is loose or hard. The take-off and landing temperature monitoring unit includes a temperature sensor (11), which monitors the temperature at the take-off and landing point and transmits the data to the PLC module through the communication module. The take-off and landing wind speed monitoring unit includes a wind speed sensor (31), which monitors the wind speed at the take-off and landing point and transmits the data to the PLC module through the communication module. The identification camera (23) captures images of the landing area. The PLC module preprocesses and extracts features from the images and uses a machine learning model to classify the ground type into one of hard ground, loose soil, grass, or sand. The PLC module also receives data from the temperature sensor (11) and the wind speed sensor (31) and determines whether the shock-absorbing airbag (8) needs to be deployed based on the ground type, temperature, and wind speed data. It also controls the drive mechanism (7) to perform deployment or retraction actions. The shock-absorbing airbag (8) is used to provide cushioning and shock absorption during landing. Each of the supporting inclined poles (3) is connected to a hydraulic damping rod (13) at its top. The hydraulic damping rod (13) is covered with a U-shaped mounting plate (28). The inner walls of both sides of the U-shaped mounting plate (28) are equipped with second air springs (29). The two second air springs (29) are fixedly connected to the outer wall of the hydraulic damping rod (13) at opposite ends.

2. The landing vibration damping frame according to claim 1, characterized in that: The ends of the two vibration damping boxes (4) are also equipped with multi-directional anti-tilt vibration damping components (18). The multi-directional anti-tilt vibration damping components (18) include anti-tilt vibration damping components (14) installed at the bottom of both ends of each vibration damping box (4) and anti-tilt vibration damping components (17) installed symmetrically on the lower part of the opposite side of the two vibration damping boxes (4).

3. A landing vibration damping frame according to claim 2, characterized in that: The ends of the two landing-side anti-tilt dampers (17) that are away from the damping housing (4) are tilted upwards, so that the back of the landing-side anti-tilt dampers (17) has an arc-shaped curved surface structure.

4. A landing vibration damping frame according to claim 3, characterized in that: Each of the anti-tilt damping components (14) before and after takeoff and landing is provided with a wave damping part (16) at the end near the damping housing (4), and an arc-shaped upturned end (15) at the end away from the damping housing (4).

5. A landing vibration damping frame according to claim 4, characterized in that: Each of the vibration damping housings (4) has a rubber vibration damping base frame (6) bonded to its bottom surface. When it is raised or lowered, the rubber vibration damping base frame (6) can provide basic buffering and vibration damping. The two rubber vibration damping base frames (6) have symmetrical holes (22) on opposite sides for the pull rope (5) to pass through.

6. An unmanned aerial vehicle, characterized in that: The unmanned aerial vehicle includes a base box (9), a top cover (10) mounted on the top of the base box (9), and a landing damping frame mounted on the bottom surface of the base box (9) as described in any one of claims 1 to 5.

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