Unmanned aerial vehicle undercarriage and unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle undercarriage and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle undercarriage comprises a first vertical pipe, a second vertical pipe, a first locking ring and a second locking ring which are coaxially arranged, the first locking ring is slidably arranged on the periphery of the first vertical pipe in a sleeving mode, and the second vertical pipe is fixedly inserted into the first locking ring; the first vertical pipe can be slidably adjusted relative to the second vertical pipe, so that the height of the undercarriage is easily adjusted, and the requirements of the unmanned aerial vehicle under different loads and working environments are met. A limiting piece is arranged on the periphery of the first locking ring, the periphery of the first locking ring is sleeved with the second locking ring, the second locking ring is in threaded connection with the first locking ring, and the second locking ring is used for being driven to drive the limiting piece to clamp the periphery of the first vertical pipe. By means of the design, it is ensured that after the undercarriage is adjusted to the needed height, the relative position between the first vertical pipe and the second vertical pipe does not change, the undercarriage is kept stable, and the weight of the unmanned aerial vehicle and pressure caused by external environment changes can be effectively borne.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a UAV landing gear and a UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and onboard program control devices. They are widely used due to their maneuverability, fast response speed, lack of human piloting, low operational requirements, and ability to carry various small devices or objects. Currently, UAVs are used in agriculture, logistics, environmental monitoring, military reconnaissance, and many other fields, with varying payload types and weights across these applications.

[0003] To meet the demands of varying payloads, drone designs are increasingly diversifying and specializing, necessitating landing gear of appropriate height and support for drones of different weights. As a crucial support system, the drone's landing gear must not only bear the drone's weight during takeoff and landing but also provide sufficient stability during taxiing, hovering, and interaction with external environmental factors. Typically, drones of different weights require landing gear of varying heights to ensure a proper match between support and gravity, guaranteeing safe operation in diverse scenarios.

[0004] However, equipping multiple landing gears of different heights increases the complexity and cost of manufacturing. On the other hand, when the drone needs to change landing gears to cope with different missions, the replacement process is cumbersome and time-consuming. This not only causes inconvenience to the daily operation and maintenance of the drone, but also affects the drone's rapid response capability and operational efficiency. Utility Model Content

[0005] The purpose of this application is to provide a drone landing gear and a drone in order to address the shortcomings of the prior art.

[0006] To achieve the above objectives, the technical solutions adopted in the embodiments of this application are as follows:

[0007] In one aspect of this application, a drone landing gear is provided, including a first vertical tube, a second vertical tube, a first locking ring, and a second locking ring coaxially arranged. The first locking ring is slidably sleeved on the outer periphery of the first vertical tube, and the second vertical tube is fixedly inserted into the first locking ring. A limiting member is provided on the periphery of the first locking ring, and the second locking ring is sleeved on the outer periphery of the first locking ring and threadedly connected to the first locking ring. The second locking ring is used to drive the limiting member to clamp the outer periphery of the first vertical tube.

[0008] Optionally, the second locking ring includes an annular threaded portion and multiple clamping portions. The multiple clamping portions are fixed to the same end of the annular threaded portion and are arranged at intervals along the circumferential direction of the annular threaded portion. The annular threaded portion is sleeved on the first vertical tube and threadedly connected to the first locking ring. The annular threaded portion is used to be driven by the multiple clamping portions to drive the limiting member to clamp the outer periphery of the first vertical tube.

[0009] Optionally, multiple clamping parts together form a conical structure, with the enlarged end of the conical structure connected to the annular threaded part, and the reduced end of the clamping part abutting against the outer periphery of the first vertical tube.

[0010] Optionally, a vertical groove is provided on the side wall of the first vertical tube, and a first protrusion is provided on the inner wall of the first locking ring, the first protrusion being slidably connected in the vertical groove.

[0011] Optionally, multiple limiting grooves are provided on the outer wall of the first vertical tube, and the multiple limiting grooves are arranged at intervals along the axial direction of the first vertical tube. The second locking ring is driven to clamp any one of the limiting grooves.

[0012] Optionally, the limiting groove is an annular groove, and multiple limiting elements are provided at intervals around the periphery of the first locking ring, with the multiple limiting elements simultaneously engaging in the same annular groove.

[0013] Optionally, the limiting element is an elastic element.

[0014] Optionally, the drone landing gear also includes a transverse tube connected to the end of the first vertical tube away from the second vertical tube, with elastic rings fitted at both ends of the transverse tube.

[0015] Optionally, the drone landing gear also includes a mounting bracket connected to the end of the second vertical tube away from the first vertical tube, the mounting bracket being used to connect the drone body to the second vertical tube.

[0016] In another aspect of this application, a drone is provided, including a drone body and any of the above-described drone landing gear, the drone landing gear being used to support the drone body.

[0017] The beneficial effects of this application include:

[0018] This application provides a drone landing gear and a drone. The drone landing gear includes a first vertical tube, a second vertical tube, a first locking ring, and a second locking ring arranged coaxially. The first locking ring is slidably sleeved on the outer periphery of the first vertical tube, and the second vertical tube is fixedly inserted into the first locking ring. This design allows the first vertical tube to slide within the first locking ring, i.e., it can be adjusted relative to the second vertical tube, thereby easily achieving height adjustment of the landing gear and meeting the needs of drones under different loads and working environments. A limiting member is provided on the periphery of the first locking ring. The second locking ring is sleeved on the outer periphery of the first locking ring and threadedly connected to the first locking ring. The second locking ring is used to drive the limiting member to clamp the outer periphery of the first vertical tube. This design ensures that after the landing gear is adjusted to the required height, the relative position between the first and second vertical tubes does not change, the landing gear remains stable, and it can effectively bear the weight of the drone and the pressure brought by changes in the external environment. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is one of the structural schematic diagrams of a drone landing gear provided in an embodiment of this application;

[0021] Figure 2 This is a second schematic diagram of the structure of a drone landing gear provided in an embodiment of this application;

[0022] Figure 3 for Figure 2 A magnified view of a portion of the image;

[0023] Figure 4 This is the third schematic diagram of a drone landing gear provided in the embodiments of this application;

[0024] Figure 5 This is one of the structural schematic diagrams provided in this application for an embodiment of a drone landing gear when the height is a first height;

[0025] Figure 6 This is the second structural schematic diagram of a drone landing gear at a first height, provided as an embodiment of this application.

[0026] Figure 7 One of the structural schematic diagrams provided in this application shows a drone landing gear with a second height.

[0027] Figure 8 This is the second structural schematic diagram of a drone landing gear at a second height, provided as an embodiment of this application.

[0028] Figure 9 This is the fourth schematic diagram of a UAV landing gear provided in the embodiments of this application;

[0029] Figure 10 This is the fifth schematic diagram of a drone landing gear provided in the embodiments of this application.

[0030] Icons: 11-First vertical tube; 11a-Vertical groove; 11b-Limiting groove; 12-Second vertical tube; 13-First locking ring; 131-Limiting component; 132-First protrusion; 14-Second locking ring; 141-Annular threaded part; 142-Clamping part; 15-Horizontal tube; 16-Elastic ring; 17-Fixing seat. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0032] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. It should be noted that, unless otherwise specified, the various features in the embodiments of this application can be combined with each other, and the combined embodiments are still within the protection scope of this application.

[0033] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0034] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this application is in use. They are only for the convenience of describing this application 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, and therefore should not be construed as a limitation on this application. In addition, the terms "first," "second," and "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0035] Furthermore, terms such as "horizontal" and "vertical" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0036] In the description of this application, it should also be noted that, unless otherwise expressly specified and limited, the terms "set up," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0037] One aspect of this application provides a drone landing gear, designed to achieve adjustable landing gear height through a simple and efficient structural design to adapt to the needs of drones with different loads. Figures 1 to 10 As shown, the landing gear includes components such as a first vertical tube 11, a second vertical tube 12, a first locking ring 13, a second locking ring 14, and a limiting member 131, which are coaxially arranged. The components cooperate with each other through specific connection relationships and technical solutions to ensure the height adjustment function and stable support effect of the landing gear.

[0038] Specifically, such as Figures 1 to 4 As shown, the basic structure of the landing gear consists of two vertical tubes, namely a first vertical tube 11 and a second vertical tube 12, which are coaxially arranged. A first locking ring 13 is slidably fitted around the outer periphery of the first vertical tube 11, and the second vertical tube 12 is fixedly inserted into the first locking ring 13. This design allows the first vertical tube 11 to slide within the first locking ring 13, that is, it can be adjusted relative to the second vertical tube 12, thereby easily achieving height adjustment of the landing gear. In this simple way, the landing gear support requirements of UAVs of different weights can be met, without the need to equip multiple landing gears of different heights.

[0039] Furthermore, limiting members 131 are provided around the periphery of the first locking ring 13. These limiting members 131 serve to fix and limit the position, ensuring the stability of the first vertical tube 11 during height adjustment. Once the landing gear is adjusted to the required height, the second locking ring 14 is fitted onto the outer periphery of the first locking ring 13. The inner wall of the second locking ring 14 is threaded, and the outer wall of the first locking ring 13 is also threaded. Tightening the second locking ring 14 creates a tight connection between the first and second locking rings, increasing the friction between the limiting members 131 and the first vertical tube 11. This clamps the limiting members 131 around the outer periphery of the first vertical tube 11, preventing further sliding. This design ensures that the relative position between the first and second vertical tubes 11 remains unchanged during use, maintaining landing gear stability and effectively bearing the weight of the UAV and the pressure from changes in the external environment.

[0040] When the landing gear height needs to be readjusted, the threaded connection between the second locking ring 14 and the first locking ring 13 can be released. By releasing the second locking ring 14, the clamping force of the limiting member 131 on the first vertical tube 11 is released, allowing the first vertical tube 11 to slide relative to the second vertical tube 12 again, thereby achieving a new height adjustment. This adjustability allows the landing gear to adapt to various UAVs with different loads and operating conditions, providing a more flexible and efficient support system.

[0041] It should be noted that, to ensure sufficient strength and durability of the landing gear, the first vertical tube 11 and the second vertical tube 12 can be made of lightweight, high-strength materials such as carbon fiber to withstand the weight of the UAV and external pressure. The first locking ring 13 and the second locking ring 14 can be made of materials such as nylon plastic to ensure their lightweight, wear resistance, and good threaded connection performance.

[0042] Through the above design, the UAV landing gear provided in this application embodiment has a high degree of adjustability and structural reliability, which can meet the needs of UAVs under different loads and working environments, simplify production and operation processes, and improve the operational efficiency and rapid response capability of UAVs.

[0043] Optionally, the limiting member 131 is an elastic member that can undergo elastic deformation or displacement when subjected to the fastening force of the second locking ring 14, thereby playing a clamping and fixing role.

[0044] Specifically, the limiting member 131 and the first vertical tube 11 can be in a clearance fit state. That is, when the tightening force of the second locking ring 14 has not yet been applied to the limiting member 131, the limiting member 131 will not generate any resistance to the sliding of the first vertical tube 11. In this state, the first vertical tube 11 can slide freely within the first locking ring 13, realizing height adjustment. This clearance fit not only ensures the smoothness of the adjustment process, but also avoids operational difficulties caused by excessive friction during adjustment. Users can easily adjust the position of the first vertical tube 11 according to their needs, making the landing gear adaptable to different loads and working conditions.

[0045] Once the landing gear is adjusted to the required height, the second locking ring 14 connects to the first locking ring 13 through its threaded fastening force, thereby applying force to the limiting member 131. During this process, the limiting member 131 undergoes elastic deformation or elastic displacement, tightly clamping itself around the outer periphery of the first vertical tube 11, thus providing a fixing function. This elastic clamping force not only effectively prevents the first vertical tube 11 from sliding relative to the second vertical tube 12, but also increases friction, thereby ensuring that the first vertical tube 11 remains fixed after height adjustment. Through the design of the elastic member, the landing gear can achieve stable support under stress, avoiding potential safety hazards to the UAV during taxiing caused by an unstable structure.

[0046] Furthermore, the elastic design of the limiting member 131 also provides high recoverability. When the landing gear height needs to be adjusted, by releasing the fastening force of the second locking ring 14, the limiting member 131 will return to its initial state, releasing the clamping force on the first vertical tube 11, thereby allowing the first vertical tube 11 to slide again for adjustment. This elastic design makes the landing gear height adjustment process both simple and efficient, enabling rapid response to the landing gear height requirements of different missions.

[0047] Optionally, such as Figure 3 As shown, the second locking ring 14 includes an annular threaded portion 141 and multiple clamping portions 142. The multiple clamping portions 142 are fixed to the same end of the annular threaded portion 141, and are arranged at intervals along the circumference of the annular threaded portion 141. The annular threaded portion 141 is sleeved on the first vertical tube 11 and threadedly connected to the first locking ring 13. The annular threaded portion 141 is used to drive the limiting member 131 to clamp the outer periphery of the first vertical tube 11 through the multiple clamping portions 142. This design, by cleverly combining the threaded connection and the clamping force, ensures that the second locking ring 14 can generate sufficient clamping force to prevent unnecessary changes in height when fixing the position of the first vertical tube 11.

[0048] Specifically, when the landing gear is adjusted to the target height, the annular threaded part 141 is screwed on and threaded to the first locking ring 13. Multiple clamping parts 142 are evenly distributed on the outer periphery of the limiting member 131. The annular threaded part 141 drives the multiple clamping parts 142 to move toward the limiting member 131, so that the multiple clamping parts 142 apply clamping force to the limiting member 131 evenly and stably along the circumferential direction. The limiting member 131 is compressed and clamped on the outer periphery of the first vertical tube 11, thereby effectively locking the first vertical tube 11 at the target height and preventing any unnecessary sliding or displacement of it relative to the second vertical tube 12.

[0049] Optionally, such as Figure 3 As shown, multiple clamping parts 142 together form a conical structure. The enlarged end of the conical structure is connected to the annular threaded part 141, and the constricted end of the clamping part 142 abuts against the outer periphery of the first vertical tube 11. With this design, the clamping part 142 can precisely adjust the clamping force on the limiting member 131 as needed, and produce a more uniform and effective clamping effect during the locking process.

[0050] First, the fit between the inner wall of the conical structure and the limiting member 131 effectively enhances the clamping force. Through this structure, the annular threaded portion 141, during rotation, drives multiple clamping portions 142 to gradually tighten inward, thereby generating a progressively increasing clamping force. The key to this process lies in the shape of the inner wall of the conical structure; the gradual contraction of the inner wall concentrates the clamping force, providing a uniform and continuous clamping action, ensuring that the limiting member 131 can be securely clamped to the outer periphery of the first vertical tube 11. This design allows the landing gear to quickly and stably lock into position during height adjustment, avoiding any slippage or loosening caused by insufficient clamping force, thus improving the stability and reliability of the entire system.

[0051] Secondly, the contact between the tapered end of the conical structure and the outer periphery of the first vertical tube 11 further enhances the locking effect. When the second locking ring 14 is fixed to the first locking ring 13 via a threaded connection, the tapered end of the conical structure abuts tightly against the outer periphery of the first vertical tube 11, maximizing the concentration of clamping force at this position. This tight contact, under the action of friction, ensures that the relative position between the first vertical tube 11 and the second vertical tube 12 will not shift, thereby further improving the stability of the landing gear. The contact design of the tapered end makes force transmission more efficient, ensuring that the first vertical tube 11 is firmly fixed at the target height, preventing any displacement that may occur under high load or vibration environments.

[0052] Optionally, such as Figure 4As shown, to prevent unnecessary rotation of the first vertical tube 11 during adjustment, a vertical groove 11a is provided on the side wall of the first vertical tube 11, and a first protrusion 132 is provided on the inner wall of the first locking ring 13. The first protrusion 132 is slidably connected in the vertical groove 11a. Through this design, the relative position between the first vertical tube 11 and the second vertical tube 12 can be effectively limited, ensuring that the first vertical tube 11 can maintain stable sliding during height adjustment, while avoiding any uncontrolled rotation and offset.

[0053] Specifically, the position and shape of the vertical slide groove 11a are matched with the height of the first protrusion 132 on the inner wall of the first locking ring 13, allowing the first protrusion 132 to precisely enter and slide within the vertical slide groove 11a. This structure not only guides the first protrusion 132 within the vertical slide groove 11a but also restricts the rotation of the first vertical tube 11 during height adjustment. The cooperation between the vertical slide groove 11a and the first protrusion 132 ensures that the first vertical tube 11 slides only vertically during adjustment, without rotating around its axis. This prevents structural instability caused by unnecessary rotation and offset, enabling the landing gear to maintain high stability under different loads and operating environments, thus improving the ease of operation and reliability of the landing gear.

[0054] Optionally, such as Figure 4 As shown, multiple limiting grooves 11b are formed on the outer wall of the first vertical tube 11. These grooves 11b are spaced apart along the axial direction of the first vertical tube 11, providing multiple adjustable locking positions for the landing gear. The second locking ring 14 is driven to clamp any of the limiting grooves 11b with the limiting member 131, thereby achieving precise locking of the landing gear at different height positions. This structural design not only improves the reliability of locking but also makes the height adjustment of the landing gear more flexible and precise.

[0055] Specifically, each limiting groove 11b is evenly arranged in the design to ensure that multiple precise selectable positions are available during landing gear adjustment. The arrangement of the limiting grooves 11b allows the first vertical tube 11 to have multiple fixed points in the axial direction, and the limiting member 131 can fix the height of the landing gear by clamping any one of the limiting grooves 11b. When the limiting member 131 is clamped in the limiting groove 11b, the tight fit between the groove wall and the limiting member 131 effectively prevents any height changes caused by external forces or vibrations, thereby ensuring the stability of the UAV landing gear. In this embodiment, two limiting grooves 11b are formed on the outer wall of the first vertical tube 11, such as... Figure 5 and Figure 6 As shown, when the limiting member 131 is clamped in the limiting groove 11b at the bottom, the landing gear height is the first height. When it is necessary to adjust the landing gear height, as... Figure 7 and Figure 8 As shown, the limiting member 131 is clamped in the limiting groove 11b at the top. At this time, the height of the landing gear is the second height, thereby realizing the height adjustment of the landing gear.

[0056] Furthermore, to further improve the convenience and accuracy of adjustments, each limit slot 11b can be marked with graduation lines, allowing users to accurately judge height changes according to their needs when adjusting the height. The graduation lines not only enhance the ease of use of the limit slots 11b but also help operators intuitively understand the current adjustment position. When adjusting the height, users can select different limit slots 11b as needed and adjust the landing gear height by clamping the corresponding limit slot 11b. This method not only makes the adjustment process more efficient but also ensures that each adjustment accurately reaches the expected height, thereby ensuring that the drone's landing gear is always in optimal working condition.

[0057] Optionally, the limiting groove 11b is an annular groove, and multiple limiting elements 131 are provided at intervals around the periphery of the first locking ring 13. The multiple limiting elements 131 are simultaneously engaged in the same annular groove, thereby forming a stable and precise limiting system.

[0058] Specifically, the annular groove ensures that the limiting member 131 remains tightly fitted against the groove wall during clamping, thereby providing a uniform and continuous clamping force. This uniform clamping force not only effectively prevents the limiting member 131 from loosening but also ensures the stability of the first vertical tube 11 during height adjustment. The annular groove structure, while ensuring accurate height adjustment, also enhances the locking effect of the entire landing gear, preventing unnecessary changes in the landing gear height when subjected to external forces or vibrations.

[0059] Meanwhile, the design of multiple limiting elements 131 further enhances the stability and durability of the locking system. Multiple limiting elements 131 engage simultaneously in the same annular groove, with each element evenly distributed at different positions within the groove, ensuring effective support and clamping force at various adjustment heights. This multi-point clamping design, by distributing force, avoids wear or deviation that might occur with a single limiting element 131 during locking, further improving the reliability of the entire system. Furthermore, the design of multiple limiting elements 131 significantly enhances the locking force of the landing gear, maintaining a stable locked state even under high loads or complex environments.

[0060] In practical application, the second vertical tube 12 is inserted into the outer wall of the first locking ring 13 and fixed by adhesive bonding. The first vertical tube 11 slides through the first locking ring 13, and the second locking ring 14 is sleeved on the outer circumference of the first vertical tube 11. During adjustment, the first vertical tube 11 is first slid to the desired height. At this time, multiple limiting members 131 are driven to align with the corresponding annular grooves. Next, by screwing the second locking ring 14, it is threadedly connected to the first locking ring 13. The tightening force of the second locking ring 14 will cause the limiting members 131 to engage in the annular groove and clamp the groove wall, thereby firmly locking the relative position between the first vertical tube 11 and the second vertical tube 12, ensuring the stability of the landing gear at the adjusted height.

[0061] Optionally, such as Figure 9 and Figure 10 As shown, the UAV landing gear also includes a transverse tube 15 connected to the end of the first vertical tube 11 away from the second vertical tube 12, with elastic rings 16 fitted at both ends of the transverse tube 15. The transverse tube 15 not only provides structural support, but also, in cooperation with the elastic rings 16, effectively reduces the impact of ground impacts and vibrations on the UAV body.

[0062] Specifically, the transverse tube 15 and the vertical tube together form a stable support frame, which can increase the overall lateral stability of the landing gear and prevent imbalance or instability during UAV landing or takeoff. The arrangement of the transverse tube 15 allows the landing gear to provide support not only in the vertical direction, but also to increase the support area on the horizontal plane, thereby improving its vibration resistance.

[0063] The primary function of the elastic ring 16 is as a shock-absorbing element, absorbing and dispersing vibrations and impacts caused by drone landing, taxiing, or external environmental factors (such as wind and uneven ground). When the drone lands on the ground, the landing gear bears a certain impact force, and the elastic ring 16, through its inherent elastic properties, can effectively buffer these impact forces, preventing vibrations from being directly transmitted to the drone body. This improves the stability of the drone when operating on complex terrain or uneven ground, reducing the potential risks from ground impacts. The elastic ring 16 is typically made of materials such as rubber or synthetic rubber with good elasticity and wear resistance.

[0064] Optionally, such as Figure 9 and Figure 10 As shown, the drone landing gear also includes a mounting base 17 connected to the end of the second vertical tube 12 away from the first vertical tube 11. The mounting base 17 is used to connect the drone body to the second vertical tube 12, thereby ensuring the overall stability of the landing gear and the drone.

[0065] The mounting base 17 is typically made of high-strength materials, such as aluminum alloy or carbon fiber, to ensure high load-bearing capacity under heavy loads and vibrations. The connection between the mounting base 17 and the second vertical tube 12 can be achieved through welding, bolting, or bonding, with the appropriate method selected based on actual needs. Regardless of the method used, the mounting base 17 must ensure a secure and reliable connection to the second vertical tube 12, preventing loosening or deformation due to external forces during use.

[0066] In another aspect of this application, a drone is provided, including a drone body and any of the aforementioned drone landing gear, the drone landing gear being used to support the drone body. Since the drone uses the aforementioned drone landing gear, it also has the same beneficial effects as a drone landing gear, which will not be elaborated further here.

[0067] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A landing gear for an unmanned aerial vehicle (UAV), characterized in that, The device includes a first vertical tube (11), a second vertical tube (12), a first locking ring (13), and a second locking ring (14) arranged coaxially. The first locking ring (13) is slidably sleeved on the outer periphery of the first vertical tube (11), and the second vertical tube (12) is fixedly inserted into the first locking ring (13). A limiting member (131) is provided on the periphery of the first locking ring (13). The second locking ring (14) is sleeved on the outer periphery of the first locking ring (13) and is threadedly connected to the first locking ring (13). The second locking ring (14) is used to drive the limiting member (131) to clamp the outer periphery of the first vertical tube (11). The second locking ring (14) includes an annular threaded portion (141) and a plurality of clamping portions (142). The plurality of clamping portions (142) are fixed to the same end of the annular threaded portion (141), and the plurality of clamping portions (142) are arranged at intervals along the circumferential direction of the annular threaded portion (141). The annular threaded portion (141) is sleeved on the first vertical tube (11) and threadedly connected to the first locking ring (13). The annular threaded portion (141) is used to be driven by the plurality of clamping portions (142) to drive the limiting member (131) to clamp the outer periphery of the first vertical tube (11). A vertical groove (11a) is provided on the side wall of the first vertical tube (11), and a first protrusion (132) is provided on the inner wall of the first locking ring (13). The first protrusion (132) is slidably connected in the vertical groove (11a).

2. The UAV landing gear according to claim 1, characterized in that, The multiple clamping parts (142) together form a conical structure, the enlarged end of the conical structure is connected to the annular threaded part (141), and the reduced end of the clamping part (142) abuts against the outer periphery of the first vertical tube (11).

3. The UAV landing gear according to claim 1 or 2, characterized in that, Multiple limiting grooves (11b) are provided on the outer wall of the first vertical tube (11). The multiple limiting grooves (11b) are arranged at intervals along the axial direction of the first vertical tube (11). The second locking ring (14) is driven to clamp any of the limiting grooves (11b) by the limiting member (131).

4. The UAV landing gear according to claim 3, characterized in that, The limiting groove (11b) is an annular groove, and multiple limiting members (131) are provided at intervals around the periphery of the first locking ring (13), and the multiple limiting members (131) are simultaneously engaged in the same annular groove.

5. The unmanned aerial vehicle landing gear according to any one of claims 1 or 2, characterized in that, The limiting member (131) is an elastic member.

6. The UAV landing gear according to claim 1 or 2, characterized in that, The UAV landing gear also includes a transverse tube (15) connected to the end of the first vertical tube (11) away from the second vertical tube (12), and elastic rings (16) are respectively fitted at both ends of the transverse tube (15).

7. The UAV landing gear according to claim 1 or 2, characterized in that, The UAV landing gear also includes a mounting base (17) connected to the end of the second vertical tube (12) away from the first vertical tube (11), the mounting base (17) being used to connect the UAV body to the second vertical tube (12).

8. A drone, characterized in that, It includes a drone body and a drone landing gear as described in any one of claims 1 to 7, wherein the drone landing gear is used to support the drone body.

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