Aircraft undercarriage and aircraft

Abstract

The invention discloses an aircraft undercarriage and an aircraft in the technical field of aircrafts, and particularly relates to a multi-buffering undercarriage for a large vertical take-off and landing unmanned aerial vehicle. The undercarriage comprises a fixing plate and two symmetrically-mounted buffer mechanisms, each buffer mechanism is composed of a connecting frame, a connecting plate, a mounting plate and a plurality of buffer assemblies, and the first buffer assembly comprises a spring and a shock absorber; the second buffer assembly is composed of a mounting block, a rotating rod, a bearing rod and an absorbing plate; the third buffering assembly is composed of a buffering part and a connecting cylinder and is connected with the rotating rod through a connecting rope to achieve dynamic buffering. In addition, rolling wheels and rubber anti-skid pads are arranged at the bottom ends of the bearing rods, and the ground contact performance is enhanced. The design effectively absorbs landing impact force, protects the unmanned aerial vehicle and equipment carried by the unmanned aerial vehicle, and improves take-off and landing safety and stability. Through multiple buffering mechanisms, the undercarriage adapts to different take-off and landing environments, the maintenance cost is reduced, and the undercarriage has wide application prospects.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, in particular to an aircraft landing gear and an aircraft. Background Art

[0002] In today's era, drone technology is developing rapidly, and its application scope has covered many fields, from aerial photography to agriculture, from plant protection to disaster relief. With its unique advantages, drones are gradually changing our traditional understanding of aircraft. Aircraft, including manned and unmanned aircraft, refer to those that can fly in the atmosphere. As a member of the aircraft family, drones are playing an increasingly important role in various fields with their flexibility and efficiency.

[0003] However, in the field of large-scale vertical take-off and landing drones, the cushioning performance of the landing gear is particularly critical. Existing designs often cannot effectively absorb the impact force during landing, which not only poses a threat to the drone itself, but also poses a potential risk to the precision equipment it carries.

[0004] In response to the above problems, this application document provides an aircraft landing gear and an aircraft to provide safer and more stable take-off and landing guarantees for large UAVs, so as to meet the growing demand for UAV applications and promote the advancement of aircraft technology. Summary of the invention

[0005] The purpose of the present invention is to solve the problems raised in the above background technology. The present invention provides an aircraft landing gear and an aircraft.

[0006] In order to achieve the above-mentioned purpose, the present invention specifically adopts the following technical solutions: An aircraft landing gear and an aircraft, comprising a fixing plate and two buffer mechanisms symmetrically mounted on the fixing plate, wherein: The buffer mechanism includes a connecting frame fixed on the fixing plate, a connecting plate fixed to the bottom end of the connecting frame, a mounting plate movably arranged below the connecting plate, at least one first buffer component connected between the mounting plate and the connecting plate, at least two second buffer components installed at the bottom of the mounting plate, and third buffer components of the same number as the second buffer components are also connected between the mounting plate and the connecting plate, and a number of the third buffer components correspond one-to-one to a number of the second buffer components, and when the second buffer component produces a buffering effect, the third buffer component produces a buffering effect.

[0007] Furthermore, the first buffer assembly includes a spring 1 connected between the mounting plate and the connecting plate.

[0008] Furthermore, the first buffer assembly also includes a shock absorber connected between the mounting plate and the connecting plate, and the spring is set on the shock absorber.

[0009] Furthermore, the second buffer component includes two mounting blocks symmetrically installed at the bottom of the mounting plate, a rotating rod is rotatably installed on the mounting block, and an inclined load-bearing rod is fixedly sleeved on the rotating rod, and the two load-bearing rods are distributed in an "eight" shape. The second buffer component also includes two absorption plates respectively fixed on the opposite sides of the mounting plate, and the two absorption plates correspond one-to-one to the two load-bearing rods. A spring 2 is connected between the opposite side of the two load-bearing rods and the two corresponding absorption plates.

[0010] Furthermore, a mounting groove is formed at the bottom end of the bearing rod, and a rolling wheel is rotatably mounted between two opposite inner walls of the mounting groove.

[0011] Furthermore, a ring-shaped rubber anti-skid pad is provided on the fixed sleeve on the circumferential side of the rolling wheel.

[0012] Furthermore, the third buffer assembly is composed of two buffer parts, which respectively correspond to the two rotating rods. The buffer part includes a connecting tube fixedly inserted vertically on the connecting plate, the top end of the connecting tube is configured with an opening and a buffer plate is movably arranged inside the connecting tube, a spring three is connected between the bottom of the buffer plate and the inner wall of the bottom end of the connecting tube, the bottom end of the connecting tube is penetrated by a through hole, and the mounting plate is penetrated by a threading hole corresponding to the through hole, a connecting rope is fixed to the bottom side of the buffer plate, one end of the connecting rope is movably penetrated through the through hole and the threading hole in turn and is fixed to the rotating rod.

[0013] Furthermore, a winding wheel is fixedly sleeved on the rotating rod, a winding groove is constructed on the outer peripheral side of the winding wheel, and one end of the connecting rope is fixed on the groove wall of the winding groove.

[0014] Furthermore, the two connecting frames are distributed in an "eight" shape, and a reinforcing rib is fixedly connected between the two connecting frames.

[0015] An aircraft comprises an aircraft body and the aircraft landing gear, wherein: a side of the fixing plate facing away from the buffer mechanism is fixed to the bottom of the aircraft body.

[0016] Compared with the prior art, the present invention has the following beneficial effects: This solution significantly improves the cushioning capacity of the landing gear through the design of multiple cushioning mechanisms. The combination of the spring and the shock absorber in the first cushioning component, and the synergistic effect of the second and third cushioning components enable the landing gear to more effectively absorb the impact force during landing and reduce damage to the UAV and its onboard equipment.

[0017] The design of the third buffer assembly in the present invention allows the landing gear to be dynamically adjusted when impacted. Through the mechanism of the connecting rope and the winding wheel, the dynamic displacement of the buffer plate is achieved to adapt to impacts of different intensities, thereby enhancing the adaptability and flexibility of the landing gear.

[0018] In the present invention, since the cushioning performance of the landing gear is enhanced, the protection ability of the drone for the precision equipment carried, such as cameras, sensors, etc., during vertical take-off and landing is also improved accordingly, reducing the risk of equipment damage. The enhanced cushioning and stability performance of the landing gear reduces the damage caused by landing impact, thereby reducing maintenance costs and repair frequency. By reducing the impact force during landing, this solution helps to improve the safety of drone operation and reduce the risk of accidents caused by landing gear failure.

[0019] The arrangement of the connecting frames and reinforcing ribs distributed in an "eight" shape in the present invention enhances the structural stability of the landing gear, making it less likely for the landing gear to deform when subjected to impact force, thereby improving the durability and reliability of the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the three-dimensional structure of the landing gear in the present invention; Figure 2 For the present invention Figure 1 A three-dimensional cross-sectional view of Figure 3 For the present invention Figure 1 Schematic diagram of the three-dimensional structure of the middle part; Figure 4 For the present invention Figure 3 A three-dimensional cross-sectional view of Figure 5 For the present invention Figure 3 A three-dimensional cross-sectional view from another direction; Figure 6 For the present invention Figure 5 A magnified view of the structure in center A; Figure 7 For the present invention Figure 3 Schematic diagram of the three-dimensional structure of the middle part; Figure 8 It is a schematic diagram of the three-dimensional structure of the aircraft in the present invention.

[0021] In the figure: 1. fixing plate; 2. buffer mechanism; 21. connecting frame; 22. connecting plate; 23. mounting plate; 231. threading hole; 24. first buffer assembly; 241. spring one; 242. shock absorber; 25. second buffer assembly; 251. mounting block; 252. rotating rod; 253. bearing rod; 254. absorption plate; 255. spring two; 256. device groove; 257. rolling wheel; 258. rubber anti-skid pad; 26. third buffer assembly; 261. connecting tube; 262. buffer plate; 263. spring three; 264. through hole; 265. connecting rope; 266. winding wheel; 267. winding groove; 27. reinforcing rib; 3. aircraft body. DETAILED DESCRIPTION

[0022] To make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0023] The present embodiment provides an aircraft landing gear and an aircraft, which are mainly used to solve the problem that the cushioning performance of the landing gear is particularly critical in the field of large-scale vertical take-off and landing UAVs. Existing designs often cannot effectively absorb the impact force during landing, which not only poses a threat to the UAV itself, but also poses a potential risk to the precision equipment it carries. The following technical solutions are provided. Figure 1-Figure 8 Make a detailed description: Example

[0024] This embodiment provides an aircraft landing gear, in particular a landing gear with multiple buffer functions designed for a large vertical take-off and landing unmanned aerial vehicle, comprising a fixing plate 1 and two buffer mechanisms 2 symmetrically mounted on the fixing plate 1, wherein: The buffer mechanism 2 includes a connecting frame 21 fixed on the fixing plate 1, a connecting plate 22 is fixed to the bottom end of the connecting frame 21, a mounting plate 23 is movably arranged below the connecting plate 22, and at least one first buffer assembly 24 is connected between the mounting plate 23 and the connecting plate 22 to provide a preliminary buffering effect. In this embodiment, the number of the first buffer assemblies 24 is two and they are symmetrically arranged; Furthermore, at least two second buffer components 25 are installed at the bottom of the mounting plate 23 to achieve the dispersion and absorption of impact force. In this embodiment, the number of the second buffer components 25 is also two and they are symmetrically arranged. The mounting plate 23 and the connecting plate 22 are also connected with third buffer components 26 of the same number as the second buffer components 25, and a plurality of third buffer components 26 correspond to a plurality of second buffer components 25 one by one. When the second buffer components 25 produce a buffering effect, the third buffer components 26 produce a buffering effect. Through this design, when the second buffer component 25 produces a buffering effect, the corresponding third buffer component 26 also produces a buffering effect synchronously, forming a multiple buffer system working in coordination. Such a design not only significantly improves the buffering capacity of the landing gear, effectively absorbs the impact force during landing, and reduces damage to the UAV and its onboard equipment, but also enhances the stability and adaptability of the landing gear, enabling it to adapt to different take-off and landing environments. In addition, this multiple buffer mechanism also helps to reduce maintenance costs, improve the safety and reliability of UAVs, and has significant practical value and market potential.

[0025] In the aircraft landing gear of the present invention, the structure and function of the first buffer assembly 24 play a vital role. Figure 2 , Figure 3 , Figure 4 and Figure 5 The first buffer assembly 24 includes a spring 241 connected between the mounting plate 23 and the connecting plate 22. The spring 241 is designed to absorb and mitigate the impact force in the vertical direction through its elastic deformation. This is the key part of the landing gear that first contacts the ground during landing. The spring 241 can effectively convert the impact force into its own elastic potential energy, thereby reducing the force directly acting on the aircraft body 3, protecting the structural safety of the UAV and the sensitive equipment carried by it. In addition, the setting of the spring 241 also helps to maintain balance when the landing gear is subjected to uneven impact, reduce the deviation or tilt caused by the impact, and ensure a smooth landing of the UAV. Through this design, the first buffer assembly 24 provides a basic buffer mechanism for the aircraft landing gear and is an important part of the entire multiple buffer system.

[0026] In the aircraft landing gear of the present invention, the first buffer assembly 24 includes not only a spring 241, but also a shock absorber 242. The shock absorber 242 is connected between the mounting plate 23 and the connecting plate 22, and the spring 241 is sleeved on the shock absorber 242. This structural design allows the shock absorber 242 to further reduce the vibration and impact caused by landing while the spring 241 absorbs the initial impact force. The function of the shock absorber 242 is to resist movement through the damping material or liquid inside the spring 241 when it is compressed or stretched, thereby reducing the vibration that may be generated by the spring 241 and providing a smoother and more stable buffering effect. The design of spring 241 being mounted on shock absorber 242 allows the two to work together. Spring 241 is responsible for storing and releasing energy, while shock absorber 242 is responsible for controlling the speed and method of energy release. This combination not only improves the landing gear's ability to absorb impact force, but also effectively reduces rebound or excessive vibration caused by excessive impact force, thereby protecting the drone and its precision equipment from damage. In addition, the presence of shock absorber 242 also helps to provide consistent cushioning performance under different landing conditions, ensuring that the drone can land safely in various environments.

[0027] In the aircraft landing gear of the present invention, the design of the second buffer assembly 25 has unique symmetry and dynamic response capability. Figure 2 , Figure 3 , Figure 4 and Figure 7 The second buffer assembly 25 includes two mounting blocks 251 symmetrically mounted on the bottom of the mounting plate 23, a rotating rod 252 is rotatably mounted on the mounting block 251, and a tilted load-bearing rod 253 is fixedly sleeved on the rotating rod 252. The two load-bearing rods 253 are distributed in an "eight" shape. This design not only enhances the stability of the structure, but also improves the resistance of the buffer assembly to lateral impact. The second buffer assembly 25 also includes two absorption plates 254 respectively fixed on the opposite sides of the mounting plate 23. The two absorption plates 254 correspond to the two load-bearing rods 253 one by one. A spring 255 is connected between the opposite side of the two load-bearing rods 253 and the two corresponding absorption plates 254. The spring 255 connection provides additional buffering and restoring force, so that the second buffer assembly 25 can quickly return to its original position after being subjected to impact, reducing damage to the drone body. The design of the spring 255 also allows the load-bearing rod 253 to have a certain elastic rebound after absorbing the impact, which helps to alleviate subsequent vibrations and provide a smoother landing experience.

[0028] For further information, see Figure 3 , Figure 4 , Figure 5 and Figure 6The third buffer assembly 26 is composed of two buffer parts, and the two buffer parts correspond to the two rotating rods 252 respectively. Such a configuration enables the third buffer assembly 26 to work in conjunction with the second buffer assembly 25 to provide a more accurate and effective buffering effect. The buffer part includes a connecting cylinder 261 fixedly inserted vertically on the connecting plate 22, the top of the connecting cylinder 261 is configured with an opening, and a buffer plate 262 is movably arranged inside the connecting cylinder 261. A spring 263 is connected between the bottom of the buffer plate 262 and the inner wall of the bottom end of the connecting cylinder 261. The existence of the spring 263 provides the buffer plate 262 with the necessary elastic force, so that the buffer plate 262 can compress the spring and absorb energy when it is impacted. The bottom end of the connecting tube 261 is penetrated with a through hole 264, and the mounting plate 23 is penetrated with a threading hole 231 corresponding to the through hole 264. A connecting rope 265 is fixed to the bottom side of the buffer plate 262. One end of the connecting rope 265 is movable through the through hole 264 and the threading hole 231 in turn and is fixed to the rotating rod 252. This design makes the movement of the buffer plate 262 and the movement of the rotating rod 252 mutually related. When the load-bearing rod 253 is impacted, it will drive the rotating rod 252 to rotate, and the connecting rope 265 will pull the buffer plate 262 accordingly, so as to achieve the buffering effect while maintaining the stability and responsiveness of the landing gear.

[0029] Furthermore, a winding wheel 266 is fixedly sleeved on the rotating rod 252. This design skillfully combines the buffer mechanism with the winding function. A winding groove 267 is constructed on the outer peripheral side of the winding wheel 266. One end of the connecting rope 265 is fixed to the groove wall of the winding groove 267. This fixing method ensures that the connecting rope 265 can be smoothly wound and released when the rotating rod 252 rotates, thereby controlling the dynamic position of the buffer plate 262. This design allows the buffer plate 262 to be effectively displaced through the synergistic effect of the connecting rope 265 and the winding wheel 266 when the landing gear is impacted, so as to absorb and mitigate the impact force. At the same time, the arrangement of the winding wheel 266 also allows the buffer plate 262 to be compactly retracted when no buffering is needed, thereby reducing the space occupied by the landing gear and improving the compactness and aerodynamic performance of the landing gear. The design of the winding wheel 266 and its winding groove 267 fixedly mounted on the rotating rod 252 not only enhances the buffering efficiency of the third buffer assembly 26, but also improves the functionality and space utilization of the landing gear. This design provides a novel buffering and storage mechanism for the aircraft landing gear, so that the landing gear can maintain a compact structure and flight efficiency while ensuring the buffering performance, further improving the take-off and landing safety and ease of operation of the UAV. Example

[0030] Embodiment 2 is a further optimization of embodiment 1 to enhance the ground adaptability and movement stability of the landing gear. Figure 3 and Figure 7 The bottom end of the supporting rod 253 is constructed with a mounting groove 256, and a rolling wheel 257 is rotatably installed between the two opposite inner walls of the mounting groove 256. This design allows the rolling wheel 257 to rotate freely in the mounting groove 256, thereby providing an additional degree of rotational freedom to adapt to uneven ground and reduce friction.

[0031] A ring-shaped rubber anti-skid pad 258 is provided on the fixed sleeve on the circumferential side of the rolling wheel 257. This design further increases the friction between the rolling wheel 257 and the ground, preventing the rolling wheel 257 from slipping when the landing gear is subjected to lateral force. The use of the rubber anti-skid pad 258 not only enhances the grip of the landing gear on wet or rough ground, but also reduces the noise generated when the rolling wheel 257 rolls on the ground, thereby improving the controllability and ride comfort of the landing gear. Example

[0032] In the aircraft landing gear of the present invention, the third embodiment is optimized with respect to the first embodiment to enhance the structural strength and stability of the landing gear. Figure 2 and Figure 8 The two connecting frames 21 are arranged in an "eight" shape. This unique layout provides better mechanical support, so that the landing gear can more evenly disperse the forces when it is subjected to vertical and horizontal forces, thereby reducing the stress borne by a single connecting frame 21; In addition, a reinforcing rib 27 is fixedly connected between the two connecting frames 21. This reinforcing structure further enhances the overall rigidity of the connecting frame 21, improves the load-bearing capacity and torsion resistance of the landing gear, and the provision of the reinforcing rib 27 not only enhances the stability of the landing gear when subjected to a large impact force, but also helps prevent the connecting frame 21 from being deformed or damaged during long-term operation. Embodiment 3 effectively improves the structural strength and stability of the landing gear through the "eight"-shaped connecting frame 21 and the additional reinforcing ribs 27. This optimized design enables the aircraft landing gear to remain stable under various take-off and landing conditions, reduces the safety risks caused by structural deformation or damage, and improves the take-off and landing safety and reliability of the UAV. Example

[0033] See also Figure 8In the aircraft landing gear system of the present invention, the fourth embodiment describes an overall structure of an aircraft, the aircraft includes an aircraft body 3 and an aircraft landing gear, specifically, a fixing plate 1, which is a key component of the landing gear system, is fixed to the bottom of the aircraft body 3 on one side facing away from the buffer mechanism 2. This layout forms a tight and stable connection between the landing gear and the aircraft body 3, ensuring that the landing gear can effectively withstand various impact forces from the vertical take-off and landing process; This installation method of the fixed plate 1 allows the buffer mechanism 2 to interact directly with the aircraft body 3, providing the necessary buffering and shock absorption functions, thereby protecting the aircraft body 3 and the sensitive equipment inside it from the impact forces generated during landing and take-off. In addition, this design also helps to simplify the installation and maintenance process of the landing gear system because it provides a clear fixing point and a direct force transmission path.

[0034] In the present invention, the aircraft landing gear system described provides an innovative multi-buffer solution for large vertical take-off and landing UAVs, which is designed to effectively absorb the impact force generated during landing and protect the UAV and its precision equipment. The following is the specific buffering process of the landing gear during take-off and landing: When the drone is ready to land, its weight and kinetic energy of falling first act on the landing gear system. The fixed plate 1, as the core structure of the landing gear, is fixed to the bottom of the aircraft body 3 on the side facing away from the buffer mechanism 2, providing a direct transmission path for the impact force. First buffering stage: the impact force is first transmitted to the second buffering assembly 25, which is composed of two symmetrically distributed load-bearing rods 253 and an absorption plate 254, which are connected by a second spring 255. When the load-bearing rod 253 is impacted, the impact force is dispersed and absorbed through the elastic action of the second spring 255, and the load-bearing rod 253 is allowed to have a certain elastic rebound to alleviate subsequent vibration. At the same time, the rotation of the load-bearing rod 253 will drive the rotation rod 252 to rotate. The rolling wheels 257 and the rubber anti-skid pads 258 improve the adaptability and movement stability of the landing gear on uneven ground, reduce friction and noise, and improve controllability and comfort; Second buffering stage: the impact received by the second buffering assembly 25 is transmitted to the first buffering assembly 24 through the mounting plate 23. The assembly includes a spring 241 and a shock absorber 242. The spring 241 absorbs the initial impact force through its elastic deformation, while the shock absorber 242 controls the oscillation of the spring 241, reduces possible rebound and excessive vibration, and provides initial buffering and shock absorption for the landing gear. The third buffering stage: the third buffering assembly 26 corresponding to the second buffering assembly 25 works synchronously, and each buffering part includes a buffering plate 262, which is connected to the connecting tube 261 through a spring three 263. When the rotating rod 252 rotates due to the action of the second buffering assembly 25, the connecting rope 265 pulls the buffering plate 262 to achieve further buffering effect. The design of the winding wheel 266 and the winding groove 267 enables the connecting rope 265 to be smoothly wound and released, thereby controlling the dynamic position of the buffering plate 262 and resetting the buffering plate 262 to prepare for the next buffering work.

[0035] It should be noted that the specific model specifications of the shock absorber 242 and the aircraft body 3 need to be selected and determined based on the actual specifications of the device, and the specific selection calculation method adopts the existing technology in this field, so it will not be described in detail. The principles of these components are clear to technical personnel in this field and do not need to be described in detail here.

[0036] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft landing gear, comprising a fixing plate (1) and two buffer mechanisms (2) symmetrically mounted on the fixing plate (1), characterized in that: in: The buffer mechanism (2) comprises a connecting frame (21) fixed on the fixing plate (1), a connecting plate (22) being fixed at the bottom end of the connecting frame (21), a mounting plate (23) being movably arranged below the connecting plate (22), at least one first buffer component (24) being connected between the mounting plate (23) and the connecting plate (22), at least two second buffer components (25) being installed at the bottom of the mounting plate (23), and third buffer components (26) being the same in number as the second buffer components (25) being connected between the mounting plate (23) and the connecting plate (22), and a plurality of the third buffer components (26) corresponding to a plurality of the second buffer components (25) one-to-one, and when the second buffer components (25) produce a buffering effect, the third buffer components (26) produce a buffering effect.

2. An aircraft landing gear according to claim 1, characterized in that: The first buffer assembly (24) comprises a spring 1 (241) connected between the mounting plate (23) and the connecting plate (22).

3. An aircraft landing gear according to claim 2, characterized in that: The first buffer assembly (24) further comprises a shock absorber (242) connected between the mounting plate (23) and the connecting plate (22), and the spring 1 (241) is sleeved on the shock absorber (242).

4. An aircraft landing gear according to claim 1, characterized in that: The second buffer component (25) comprises two mounting blocks (251) symmetrically mounted on the bottom of the mounting plate (23); a rotating rod (252) is rotatably mounted on the mounting block (251); a bearing rod (253) which is arranged obliquely is fixedly sleeved on the rotating rod (252); the two bearing rods (253) are arranged in an "eight" shape; the second buffer component (25) further comprises two absorption plates (254) respectively fixed on opposite sides of the mounting plate (23); the two absorption plates (254) correspond one to one with the two bearing rods (253); and a second spring (255) is connected between the opposite sides of the two bearing rods (253) and the two corresponding absorption plates (254).

5. An aircraft landing gear according to claim 4, characterized in that: The bottom end of the bearing rod (253) is formed with a mounting groove (256), and a rolling wheel (257) is rotatably mounted between two opposite inner walls of the mounting groove (256).

6. An aircraft landing gear according to claim 5, characterized in that: An annular rubber anti-skid pad (258) is fixedly sleeved on the circumferential side of the rolling wheel (257).

7. An aircraft landing gear according to claim 4, characterized in that: The third buffer assembly (26) is composed of two buffer parts, and the two buffer parts correspond to the two rotating rods (252) respectively. The buffer part includes a connecting tube (261) fixedly inserted vertically on the connecting plate (22), the top end of the connecting tube (261) is configured with an opening, and a buffer plate (262) is movably arranged inside the connecting tube (261), a spring three (263) is connected between the bottom of the buffer plate (262) and the inner wall of the bottom end of the connecting tube (261), the bottom end of the connecting tube (261) is penetrated by a through hole (264), the mounting plate (23) is penetrated by a threading hole (231) corresponding to the through hole (264), a connecting rope (265) is fixed to the bottom side of the buffer plate (262), and one end of the connecting rope (265) is movably passed through the through hole (264) and the threading hole (231) in turn and is fixed to the rotating rod (252).

8. An aircraft landing gear according to claim 7, characterized in that: A winding wheel (266) is fixedly sleeved on the rotating rod (252), a winding groove (267) is constructed on the outer peripheral side of the winding wheel (266), and one end of the connecting rope (265) is fixed to the groove wall of the winding groove (267).

9. An aircraft landing gear according to claim 1, characterized in that: The two connecting frames (21) are distributed in an "eight" shape, and a reinforcing rib (27) is fixedly connected between the two connecting frames (21).

10. An aircraft, characterized in that: It comprises an aircraft body (3) and an aircraft landing gear according to any one of claims 1 to 9, wherein the side of the fixing plate (1) facing away from the buffer mechanism (2) is fixed to the bottom of the aircraft body (3).

Images