Take-off and landing vibration reduction structure of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle takeoff and landing damping structure, belongs to the technical field of unmanned aerial vehicles, solves the problem that the soil slope is inconvenient to adjust, and comprises a landing gear body, a damping mechanism is fixedly connected to the outer surface of the landing gear body, and a maintenance mechanism is rotationally connected to the outer surface of the damping mechanism. The damping mechanism comprises a fixing block fixedly connected to the outer surface of the undercarriage body, and the outer surface of the fixing block is in threaded connection with a threaded rod. When a positioning block rotates, a damping telescopic rod and a fixing block are driven to rotate, then the distance between a limiting plate and the fixing block is adjusted, the initial compression state of a spring is changed so as to adapt to impact force of different strengths, the connecting ring is carefully moved out of a sliding groove step by step by pulling the connecting ring, and the service life of the connecting ring is prolonged. Therefore, a maintainer can check, maintain and replace key damping components such as a spring, a damping telescopic rod, a threaded rod and the like without obstacles.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a vibration reduction structure for UAV take-off and landing. Background Technology

[0002] With the rapid development of drone technology, its application areas are constantly expanding, from common aerial photography and surveying to emerging scenarios such as logistics delivery and emergency rescue. The use of drones is becoming increasingly frequent. However, existing drone landing gear is struggling to meet the diverse operational needs. Traditional landing gear often uses a simple rigid structure, which cannot effectively buffer impact forces during landing, leading to frequent damage to the drone's airframe and internal equipment, resulting in high maintenance costs. As drones increasingly perform missions in complex terrain environments, such as mountains, jungles, and wetlands, rigid landing gear struggles to adapt to uneven and soft ground, often causing unstable landing attitudes or even tipping accidents, seriously affecting mission execution and equipment safety.

[0003] Because existing drone landing gears have different requirements in different operating scenarios, a single mode of cushioning is difficult to adapt to the impact changes brought about by different ground conditions such as flat cement ground, soft sand, and undulating grass. Therefore, there is a problem of not being able to adapt to impacts of different intensities. Utility Model Content

[0004] (a) Technical problems to be solved

[0005] To address the problems existing in the prior art, this utility model provides a vibration reduction structure for the take-off and landing of unmanned aerial vehicles (UAVs).

[0006] (II) Technical Solution

[0007] To achieve the above objectives, this utility model provides the following technical solution: a vibration damping structure for unmanned aerial vehicle (UAV) takeoff and landing, comprising a landing gear body, a vibration damping mechanism fixedly connected to the outer surface of the landing gear body, and a maintenance mechanism rotatably connected to the outer surface of the vibration damping mechanism. The vibration damping mechanism includes a fixing block fixedly connected to the outer surface of the landing gear body, a threaded rod threadedly connected to the outer surface of the fixing block, a connecting block fixedly connected to the lower surface of the threaded rod, a damping telescopic rod fixedly connected to the lower surface of the connecting block, and a spring abutting the lower surface of the fixing block. The maintenance mechanism includes a protective sleeve rotatably connected to the outer surface of the fixing block, a sliding groove formed on the outer surface of the fixing block, a connecting ring rotatably connected to the outer surface of the sliding groove, the outer surface of the connecting ring fixedly connected to the inner wall of the protective sleeve, and a limit plate fixedly connected to the inner wall of the protective sleeve.

[0008] In a preferred embodiment of the unmanned aerial vehicle (UAV) take-off and landing vibration reduction structure of the present invention, a positioning block is fixedly connected to the other end of the damping telescopic rod, and a limit block is fixedly connected to the lower surface of the positioning block.

[0009] By adopting the above technical solution, the positioning block rotates, which drives the damping telescopic rod and the fixed block to rotate, thereby facilitating the adjustment of the distance between the limiting plate and the fixed block.

[0010] As a preferred embodiment of the unmanned aerial vehicle (UAV) take-off and landing vibration reduction structure of the present invention, the outer surface of the limiting block is slidably connected to the upper surface of the limiting plate, and the limiting block adopts a square structure.

[0011] By adopting the above technical solution, the limiting plate and the positioning block can rotate synchronously through the limiting block.

[0012] In a preferred embodiment of the unmanned aerial vehicle (UAV) take-off and landing vibration reduction structure described in this utility model, the lower surface of the spring is engaged with the upper surface of the limiting plate.

[0013] By adopting the above technical solution, the spring and the upper surface of the limiting plate are snapped together, which facilitates the maintenance of the spring.

[0014] In a preferred embodiment of the unmanned aerial vehicle (UAV) takeoff and landing vibration reduction structure described in this utility model, the cross-section of the connecting ring is a convex-shaped structure.

[0015] By adopting the above technical solution, the connecting ring facilitates the prevention of separation between the connecting ring and the fixing block, and the connecting ring is elastic, making it easy to install the connecting ring on the outer surface of the fixing block.

[0016] As a preferred embodiment of the unmanned aerial vehicle (UAV) take-off and landing vibration reduction structure of this utility model, the upper surface of the limiting plate is provided with a square limiting groove that matches the outer surface of the limiting block, and the limiting groove is slidably connected to the outer surface of the limiting block.

[0017] By adopting the above technical solution, the limiting groove facilitates the limiting of the limiting block.

[0018] (III) Beneficial Effects

[0019] This utility model provides a vibration reduction structure for takeoff and landing of unmanned aerial vehicles (UAVs). It has the following beneficial effects:

[0020] 1. When the positioning block rotates, it drives the damping telescopic rod and the fixed block to rotate, thereby adjusting the distance between the limit plate and the fixed block, changing the initial compression state of the spring, and thus adapting to impact forces of different intensities.

[0021] 2. By pulling the connecting ring to overcome its elastic resistance, carefully move the connecting ring out of the sliding groove to disconnect the protective sleeve from the fixed block. Once the connecting ring is detached, the protective sleeve can be easily removed, fully exposing the shock absorption mechanism. This allows maintenance personnel to inspect, maintain, and replace key shock absorption components such as springs, damping telescopic rods, and threaded rods without any obstacles. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0024] Figure 2 This is a front view of the overall structure of this utility model;

[0025] Figure 3 yes Figure 2 A magnified structural diagram of A in the middle;

[0026] Figure 4 yes Figure 2 A magnified structural diagram of B in the diagram.

[0027] In the diagram, 1 is the landing gear body; 2 is the maintenance mechanism; 201 is the protective sleeve; 202 is the connecting ring; 203 is the sliding groove; 204 is the limiting groove; 205 is the limiting plate; 3 is the shock absorption mechanism; 301 is the fixing block; 302 is the threaded rod; 303 is the connecting block; 304 is the damping telescopic rod; 305 is the spring; 306 is the limiting block; and 307 is the positioning block. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention.

[0029] Example 1

[0030] Reference Figure 1 , Figure 2 , Figure 3 and Figure 4This is the first embodiment of the present invention. This embodiment provides a vibration damping structure for the take-off and landing of an unmanned aerial vehicle (UAV), including a landing gear body 1. A damping mechanism 3 is fixedly connected to the outer surface of the landing gear body 1. A maintenance mechanism 2 is rotatably connected to the outer surface of the damping mechanism 3. The damping mechanism 3 includes a fixing block 301 fixedly connected to the outer surface of the landing gear body 1. A threaded rod 302 is threadedly connected to the outer surface of the fixing block 301. A connecting block 303 is fixedly connected to the lower surface of the threaded rod 302. A damping telescopic rod 304 is fixedly connected to the lower surface of the connecting block 303. A spring 305 is attached to the lower surface of the fixing block 301.

[0031] The other end of the damping telescopic rod 304 is fixedly connected to a positioning block 307. The lower surface of the positioning block 307 is fixedly connected to a limit block 306. The outer surface of the limit block 306 is slidably connected to the upper surface of the limit plate 205. The limit block 306 adopts a square structure. The lower surface of the spring 305 is engaged with the upper surface of the limit plate 205.

[0032] Furthermore, upon the moment the drone touches the ground, the impact force first acts on the landing gear body 1. The landing gear body 1 transmits the force to the shock absorption mechanism 3. The fixed block 301, fixed to the outer surface of the landing gear body 1, serves as a basic support component. The threaded rod 302, which is threaded to it, plays a key adjustment role. The connecting block 303 and the damping telescopic rod 304 connected below the threaded rod 302, together with the spring 305 attached to the bottom of the fixed block 301, work together to absorb shock. As the impact force arrives, the spring 305 is compressed, using its own elastic deformation to convert part of the impact force into elastic potential energy for storage, thus achieving an initial buffering effect. At the same time, during the extension and retraction process, the damping telescopic rod 304 consumes energy through the action of the internal damping medium, slowing down the rebound speed of the spring 305 and avoiding secondary impact. When the positioning block 307 rotates, it drives the damping telescopic rod 304 and the fixed block 301 to rotate, thereby adjusting the distance between the limiting plate 205 and the fixed block 301, changing the initial compression state of the spring 305, and thus adapting to impact forces of different intensities.

[0033] Example 2

[0034] Reference Figure 1 , Figure 2 , Figure 3 and Figure 4 This is the second embodiment of the present invention. This embodiment is based on the previous embodiment. The maintenance mechanism 2 includes a protective sleeve 201 rotatably connected to the outer surface of the fixed block 301. A sliding groove 203 is provided on the outer surface of the fixed block 301. A connecting ring 202 is rotatably connected to the outer surface of the sliding groove 203. The outer surface of the connecting ring 202 is fixedly connected to the inner wall of the protective sleeve 201. A limit plate 205 is fixedly connected to the inner wall of the protective sleeve 201.

[0035] The cross-section of the specific connecting ring 202 is a convex structure. The upper surface of the limiting plate 205 is provided with a square limiting groove 204 that matches the outer surface of the limiting block 306. The limiting groove 204 is slidably connected to the outer surface of the limiting block 306.

[0036] By further pulling the connecting ring 202 to overcome its elastic resistance, the connecting ring 202 can be carefully moved out of the sliding groove 203, thus detaching the protective sleeve 201 from the fixing block 301. Once the connecting ring 202 is detached, the protective sleeve 201 can be easily removed, fully exposing the shock absorption mechanism 3, allowing maintenance personnel to inspect, maintain, and replace key shock absorption components such as the spring 305, damping telescopic rod 304, and threaded rod 302 without any obstacles.

[0037] Working principle: First, spring 305 is snapped onto the upper surface of limiting plate 205. Then, threaded rod 302 is threaded onto the outer surface of landing gear body 1. Next, limiting groove 204 is fitted onto the outer surface of limiting block 306, which facilitates limiting of limiting block 306 and positioning block 307. Then, connecting ring 202 is slid to the outer surface of sliding groove 203. By rotating limiting plate 205, the rotation of limiting plate 205 drives limiting block 306 and positioning block 307 to rotate. The rotation of positioning block 307 drives damping telescopic rod 304, connecting block 303 and threaded rod 302 to rotate, so that threaded rod 302 moves into the interior of landing gear body 1, which facilitates adjustment of the tension of spring 305.

[0038] It should be noted that in this document, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

Claims

1. A vibration damping structure for takeoff and landing of an unmanned aerial vehicle (UAV), comprising a landing gear body (1), characterized in that: The outer surface of the landing gear body (1) is fixedly connected to a shock-absorbing mechanism (3), and the outer surface of the shock-absorbing mechanism (3) is rotatably connected to a maintenance mechanism (2); The shock absorption mechanism (3) includes a fixing block (301) fixedly connected to the outer surface of the landing gear body (1), a threaded rod (302) threadedly connected to the outer surface of the fixing block (301), a connecting block (303) fixedly connected to the lower surface of the threaded rod (302), a damping telescopic rod (304) fixedly connected to the lower surface of the connecting block (303), and a spring (305) attached to the lower surface of the fixing block (301). The maintenance mechanism (2) includes a protective sleeve (201) rotatably connected to the outer surface of the fixed block (301), and a sliding groove (203) is provided on the outer surface of the fixed block (301). A connecting ring (202) is rotatably connected to the outer surface of the sliding groove (203). The outer surface of the connecting ring (202) is fixedly connected to the inner wall of the protective sleeve (201), and a limit plate (205) is fixedly connected to the inner wall of the protective sleeve (201).

2. The unmanned aerial vehicle (UAV) takeoff and landing vibration reduction structure according to claim 1, characterized in that: The other end of the damping telescopic rod (304) is fixedly connected to a positioning block (307), and a limit block (306) is fixedly connected to the lower surface of the positioning block (307).

3. The unmanned aerial vehicle (UAV) takeoff and landing vibration reduction structure according to claim 2, characterized in that: The outer surface of the limiting block (306) is slidably connected to the upper surface of the limiting plate (205), and the limiting block (306) adopts a square structure.

4. The unmanned aerial vehicle (UAV) takeoff and landing vibration reduction structure according to claim 3, characterized in that: The lower surface of the spring (305) is engaged with the upper surface of the limiting plate (205).

5. The unmanned aerial vehicle (UAV) takeoff and landing vibration reduction structure according to claim 4, characterized in that: The cross-section of the connecting ring (202) is a convex shape.

6. The unmanned aerial vehicle (UAV) takeoff and landing vibration reduction structure according to claim 5, characterized in that: The upper surface of the limiting plate (205) is provided with a square limiting groove (204) that matches the outer surface of the limiting block (306). The limiting groove (204) is slidably connected to the outer surface of the limiting block (306).

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