Unmanned aerial vehicle undercarriage

Abstract

The utility model provides an undercarriage of an unmanned aerial vehicle. The undercarriage comprises an upper fixing plate, a lower fixing plate, supporting legs and a buffer mechanism, the upper fixing plate is connected with the lower fixing plate; the supporting legs are connected with the lower fixing plate through buffer mechanisms; the buffer mechanism comprises a spring and a damping sleeve; the spring is mounted in the damping sleeve; first positioning grooves are formed in the lower end faces of the joints of the supporting legs and the lower fixing plate. A second positioning groove corresponding to the first positioning groove is formed in the upper end face of the lower fixing plate. The damping sleeve is mounted between the first positioning groove and the second positioning groove; rotating shafts are arranged on the supporting legs; a shaft hole corresponding to the rotating shaft is formed in the lower fixing plate; the supporting legs are rotationally connected with the lower fixing plate through the rotating shafts and the shaft holes; the buffer structure is simple in structure and convenient and fast to operate, the damping sleeve in the buffer structure can effectively reduce the corrosion probability of the spring, and the damping sleeve in clearance fit is convenient and fast to disassemble and assemble.

Description

Technical Field

[0001] The utility model belongs to the technical field of UAV accessories, and particularly relates to a landing gear of a UAV. Background Art

[0002] An unmanned aerial vehicle, abbreviated as "UAV", is an unpiloted aircraft controlled by a radio remote control device and a self - contained program control device, or is operated completely or intermittently autonomously by an on - vehicle computer. The landing gear of a UAV is installed at the bottom of the UAV body to support the body upward, and is an important component that can ensure the safe landing and take - off stability of the UAV.

[0003] The existing UAV landing gears mainly have three forms: an integral bracket, a sled - type bracket, and a strut - type bracket. The integral bracket is suitable for light UAVs. The sled - type bracket has a large static load, and the strut - type bracket has good structural rigidity and a large load. However, the shock - absorption performance of the above landing gears during use is poor. When the UAV lands, due to its own weight, there is a large impact force during landing, which easily causes the UAV to tilt, and then the wings or the body are damaged. Although some UAVs in the prior art add springs to the landing gear for buffering, the springs are exposed outside, and are extremely easy to rust after flying in rainy days, affecting the shock - absorption effect of the UAV, and the springs of the existing shock - absorption brackets are inconvenient to replace.

[0004] For example, the UAV landing gear with the authorization announcement number CN220010124U includes a mounting plate. The upper end of the mounting plate is provided with a UAV base, and the mounting plate and the UAV base are fixedly connected through a UAV landing gear fixing mechanism. The lower end side of the mounting plate is provided with a connecting column, and the lower end of the connecting column is provided with a first connecting plate, and the lower end of the first connecting plate is provided with an electric push rod.

[0005] For the above - disclosed UAV landing gear, it buffers the UAV by setting a buffer spring on the landing gear. However, the buffer spring of this device is exposed outside and is prone to rust after flying in rainy days, resulting in the leg being stuck, and the buffer spring sleeved on the leg is inconvenient to replace, affecting the convenience of the device. Therefore, a UAV landing gear is needed to solve the above problems. Summary of the Utility Model

[0006] Aiming at the above problems, the purpose of the present utility model is to provide a UAV landing gear with the advantages of good shock - absorption performance and convenient maintenance, which solves the problems of poor shock - absorption effect of the UAV landing gear, easy rusting and difficult replacement of the shock - absorption spring of the UAV landing gear.

[0007] The present utility model is realized through the following technical solutions:

[0008] An unmanned aerial vehicle landing gear, comprising an upper fixing plate, a lower fixing plate, a leg and a buffer mechanism; the upper fixing plate is connected to the lower fixing plate; the leg is connected to the lower fixing plate through the buffer mechanism; the buffer mechanism includes a spring and a damping sleeve; the spring is installed inside the damping sleeve; a first positioning groove is provided on the lower end surface at the connection of the leg and the lower fixing plate; a second positioning groove corresponding to the first positioning groove is provided on the upper end surface of the lower fixing plate; the damping sleeve is installed between the first positioning groove and the second positioning groove; a rotating shaft is provided on the leg; a shaft hole corresponding to the rotating shaft is provided on the lower fixing plate; the leg and the lower fixing plate are rotationally connected through the rotating shaft and the shaft hole; the damping sleeve is a hollow rubber column; the outer surface of the damping sleeve is a corrugated structure; an exhaust hole one is provided at the bottom of the damping sleeve; an exhaust hole two corresponding to the exhaust hole one is provided at the bottom of the second positioning groove; a ventilation hole is provided on the side surface of the leg; a reinforcing rib is provided inside the ventilation hole; a hook is provided at the center of the bottom of the upper fixing plate; a through hole is provided at the center of the bottom of the lower fixing plate; an internal thread sleeve is provided at the bottom of the upper fixing plate, a threaded rod is provided at the top of the hook, and the hook and the upper fixing plate are connected through the threaded rod and the internal thread sleeve

[0009] The beneficial effects of the present utility model:

[0010] The structure of the present utility model is simple, the operation is convenient and fast, the damping sleeve in the buffer structure can effectively reduce the corrosion probability of the spring, and the damping sleeve with clearance fit is convenient for quick disassembly and installation. Description of the drawings

[0011] The following further describes the present utility model in detail with reference to the drawings.

[0012] Figure 1 is the structural schematic diagram of the present utility model.

[0013] Figure 2 is the exploded view of the present utility model.

[0014] Figure 3 is the connection schematic diagram of the leg and the lower fixing plate in the present utility model.

[0015] Figure 4 is the cross-sectional view schematic diagram of the present utility model.

[0016] Figure 5 is Figure 4 the partial enlarged view of A in

[0017] As shown in the figure: 1 - upper fixing plate; 101 - internal thread sleeve; 102 - lifting hook; 103 - threaded rod; 2 - lower fixing plate; 201 - shaft hole; 202 - second positioning groove; 203 - through hole; 204 - second exhaust hole; 3 - leg; 301 - rotating shaft; 302 - ventilation hole; 303 - reinforcing rib; 304 - first positioning groove; 4 - buffer mechanism; 401 - damping sleeve; 402 - spring; 403 - first exhaust hole. Detailed implementation mode

[0018] The following specific embodiments illustrate the implementation mode of the present utility model. Those skilled in the art can easily understand other advantages and effects of the present utility model from the content disclosed in this specification.

[0019] It should be noted that the structures, proportions, sizes, etc. shown in the attached drawings of this specification are only used to cooperate with the content disclosed in the specification for those skilled in the art to understand and read, and are not used to limit the limited conditions under which the present utility model can be implemented. Therefore, they do not have any technical essence. Any modification of the structure, change of the proportional relationship, or adjustment of the size, without affecting the effects that the present utility model can produce and the purposes that can be achieved, should still fall within the scope covered by the technical content disclosed in the present utility model. At the same time, the terms such as "upper", "lower", "left", "right", "middle", etc. cited in this specification are only for the convenience of description and are not used to limit the scope under which the present utility model can be implemented. The change or adjustment of their relative relationships, without substantial change in the technical content, should also be regarded as the scope under which the present utility model can be implemented.

[0020] In the description of the present utility model, it should be noted that unless otherwise clearly specified and limited, the terms "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations. It should be noted that the terms "including", "comprising" or any other variant are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not clearly listed, or also includes elements inherent to such a process, method, article or device.

[0021] Such as Figures 1 - 5The shown landing gear of the drone includes: an upper fixing plate 1, an internal thread sleeve 101, a hook 102, a threaded rod 103, a lower fixing plate 2, a shaft hole 201, a second positioning groove 202, a through hole 203, an exhaust hole two 204, and a leg; 301 - a rotating shaft; 302 - a ventilation hole; 303 - a reinforcing rib; 304 - a first positioning groove; 4 - a buffer mechanism; 401 - a damping sleeve; 402 - a spring; 403 - an exhaust hole one.

[0022] The upper fixing plate 1 and the lower fixing plate 2 are fixedly connected by bolts;

[0023] The leg 3 is connected to the lower fixing plate 2 through a buffer mechanism 4; ventilation holes 302 are provided on the side of the leg 3, and multiple groups of ventilation holes 302 are provided on the leg 3 to reduce the wind resistance during the turning of the drone, and at the same time reduce the weight of the leg 3 and improve the load of the drone; reinforcing ribs 303 are provided in the ventilation holes 302, and through the reinforcing ribs 303, the anti-bending ability of the leg 3 is further enhanced, and the structural strength of the leg 3 is improved.

[0024] The buffer mechanism 4 includes a spring 402 and a damping sleeve 401; the spring 402 is installed inside the damping sleeve 401; a first positioning groove 304 is provided on the lower end surface at the connection between the leg 3 and the lower fixing plate 2; a second positioning groove 202 corresponding to the first positioning groove 304 is provided on the upper end surface of the lower fixing plate 2; the damping sleeve 401 is installed between the first positioning groove 304 and the second positioning groove 202; a rotating shaft 301 is provided on the leg 3; a shaft hole 201 corresponding to the rotating shaft 301 is provided on the lower fixing plate 2; the leg 3 and the lower fixing plate 2 are rotatably connected through the rotating shaft 301 and the shaft hole 201.

[0025] The damping sleeve 401 is a hollow rubber column; the outer surface of the damping sleeve 401 is a corrugated structure; an exhaust hole one 403 is provided at the bottom of the damping sleeve 401; an exhaust hole two 204 corresponding to the exhaust hole one 403 is provided at the bottom of the second positioning groove 202; when the damping sleeve 401 is squeezed, the damping sleeve 401 slowly exhausts air through the exhaust hole one 403 and the exhaust hole two 204, so as to cooperate with the internal spring 402 to form damping shock absorption, avoiding the leg 3 from rebounding repeatedly under the action of the spring 402 and causing severe shaking of the drone, and the damping sleeve 401 is sleeved on the outer end of the spring 402, which can effectively prevent the spring 402 from being affected by moisture and rust, and improve the service life of the spring 402; the damping sleeve 401 has a clearance fit with the first positioning groove 304 and the second positioning groove 202, avoiding deviation and dropping during its use, and at the same time facilitating the quick disassembly of the damping sleeve 401, so as to replace it, improving the convenience of the equipment.

[0026] A hook 102 is provided at the center of the bottom of the upper fixing plate 1; a through hole 203 is provided at the center of the bottom of the lower fixing plate 2. By providing a hook 102 at the lower end of the landing gear, it is convenient for the equipment to suspend goods, eliminating the need for an externally installed towing component and improving the load-bearing capacity of the equipment. An internal thread sleeve 101 is provided at the bottom of the upper fixing plate 1, and a threaded rod 103 is provided at the top of the hook 102. The hook 102 is connected to the upper fixing plate 1 through the threaded rod 103 and the internal thread sleeve 101, enabling the hook 102 to be adjusted up and down. When the drone needs to suspend goods, first rotate the hook 102 counterclockwise to move the hook 102 downward, suspend the goods on the hook 102, and then tighten the hook 102 clockwise to retract the hook 102 between the upper fixing plate 1 and the lower fixing plate 2. Thus, through the limitation of the through hole 203, the goods are prevented from slipping off the hook 102.

[0027] Working principle:

[0028] During use, first, install the upper fixing plate 1 on the bottom of the drone through bolts. When the drone lands, the bottom of the leg 3 rotates upward along the rotating shaft 301, so that the top of the leg 3 presses against the buffer mechanism 4. Through the cooperation of the spring 402 and the damping sleeve 401, buffer force is dissipated to reduce the vibration amplitude of the drone. When the spring 402 in the damping sleeve 401 ages, forcefully pull out the damping sleeve 401 from the gap between the upper fixing plate 1 and the lower fixing plate 2. Then, insert a new buffer mechanism 4 between the upper fixing plate 1 and the lower fixing plate 2, and finely adjust the top and bottom of the damping sleeve 401 in sequence, so that the top of the damping sleeve 401 is inserted into the first positioning groove 304, and the bottom of the damping sleeve 401 is inserted into the second positioning groove 202. It is also possible to remove the bolts between the upper fixing plate 1 and the lower fixing plate 2, remove the lower fixing plate 2, and replace the buffer mechanism 4.

[0029] The protection scope of the present utility model is not limited to the technical solutions disclosed in the specific embodiments. Any modifications, equivalent replacements, improvements, etc. made to the above embodiments based on the technical essence of the present utility model shall fall within the protection scope of the present utility model.

Claims

1. An unmanned aerial vehicle landing gear, characterized in that: It includes an upper fixing plate (1), a lower fixing plate (2), legs (3) and a buffer mechanism (4); the upper fixing plate (1) is connected to the lower fixing plate (2); the legs (3) are connected to the lower fixing plate (2) through the buffer mechanism (4); the buffer mechanism (4) includes a spring (402) and a damping sleeve (401); the spring (402) is installed inside the damping sleeve (401); a first positioning groove (304) is provided on the lower end surface at the connection of the leg (3) and the lower fixing plate (2); a second positioning groove (202) corresponding to the first positioning groove (304) is provided on the upper end surface of the lower fixing plate (2); the damping sleeve (401) is installed between the first positioning groove (304) and the second positioning groove (202); a rotating shaft (301) is provided on the leg (3); a shaft hole (201) corresponding to the rotating shaft (301) is provided on the lower fixing plate (2); the leg (3) and the lower fixing plate (2) are rotatably connected through the rotating shaft (301) and the shaft hole (201); the damping sleeve (401) has a clearance fit with the first positioning groove (304) and the second positioning groove (202).

2. The landing gear of an unmanned aerial vehicle according to claim 1, characterized in that: The damping sleeve (401) is a hollow rubber column; the outer surface of the damping sleeve (401) is a corrugated structure; an exhaust hole one (403) is provided at the bottom of the damping sleeve (401); an exhaust hole two (204) corresponding to the exhaust hole one (403) is provided at the bottom of the second positioning groove (202).

3. The landing gear of a drone according to claim 1, characterized in that: A ventilation hole (302) is provided on the side surface of the leg (3).

4. The landing gear of a drone according to claim 3, wherein: Reinforcing ribs (303) are provided inside the ventilation hole (302).

5. The undercarriage of an unmanned aerial vehicle according to claim 1, characterized in that: A hook (102) is provided at the center of the bottom of the upper fixing plate (1); a through hole (203) is provided at the center of the bottom of the lower fixing plate (2).

6. The undercarriage of a drone according to claim 5, characterized in that: An internal thread sleeve (101) is provided at the bottom of the upper fixing plate (1), a threaded rod (103) is provided at the top of the hook (102), and the hook (102) is connected to the upper fixing plate (1) through the threaded rod (103) and the internal thread sleeve (101).

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