Unmanned aircraft wing tube connecting structure

Abstract

The utility model discloses an unmanned aerial vehicle wing pipe connecting structure, including the sleeve, the outside wall of sleeve is equipped with the convex ring of annular structure, is equipped with the eccentric groove in the sleeve, is equipped with the movable slot on the convex ring, the radial inboard end of movable slot is in communication with the radial outside end of eccentric groove, and the eccentric groove is movably provided with locking piece, and the outer contour of locking piece in eccentric groove region is matched with the inner contour of eccentric groove, locking piece is close to the one end of cutting entry and is the end of sticking together, and the other end is the limiting end, and the thickness of locking piece gradually thickens from the end of sticking together to the limiting end, and the radial outside of one side of locking piece close to the limiting end is provided with the boss through movable slot, and the boss is connected with locking bolt, locking piece can eccentrically rotate inwards and carry out the end of sticking together of the round pipe wing in the sleeve, and locking bolt can carry out the longitudinal tightness adjustment between the round pipe wing and locking piece.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV wing tube connection structure. Background Technology

[0002] In recent years, drone technology has developed rapidly, and its application scenarios have gradually expanded from the initial field of military reconnaissance to various aspects of the civilian sector. In the agricultural field, agricultural drones, with their efficient and precise operating capabilities, have become an important tool for the mechanization and intelligent development of modern agriculture. Agricultural drones can carry large loads for lifting and transporting crops, and can also carry pesticides for regional spraying operations, greatly improving agricultural production efficiency and reducing labor costs.

[0003] With the increasing number of drone applications, the demand for drone transportation is also becoming more prominent. Especially in cross-regional operations or long-distance transportation, in order to reduce transportation costs and improve transportation efficiency, drones are required to minimize their size during transportation to facilitate loading and storage.

[0004] Existing agricultural drones typically have a large fuselage structure. To facilitate storage and transportation, their arms are generally made of round tubes. These round tube arms often use a horizontal folding design, generally requiring motor mounts, folding components, and mounting bases connected to the center plate. The use of these connectors not only increases the overall weight and cost but also requires leveling during installation, demanding a high level of assembly skill. Furthermore, some folding components use a press-fit buckle style, which can easily develop play in the air over long-term use, affecting flight stability and safety. Utility Model Content

[0005] This invention provides a wing tube connection structure for unmanned aerial vehicles (UAVs), which helps to solve the problem that structural wear is easily caused by the folding method used for wing storage in some current UAVs.

[0006] This utility model is implemented as follows:

[0007] An unmanned aerial vehicle wing tube connection structure includes a sleeve. The sleeve is provided with a sleeve hole having an axial through-hole structure, and the sleeve hole is for inserting and connecting a circular tube wing of an unmanned aerial vehicle. A convex ring with a ring structure is provided on the outer side wall of the sleeve. An eccentric groove is provided in the inner region of the sleeve located inside the convex ring. The longitudinal profile of the eccentric groove is in a "C" shape structure, and the inner end of the eccentric groove is a cut-in port communicating with the sleeve hole. A movable groove with a radial through-hole structure is provided on the convex ring, and the radially inner end of the movable groove communicates with the radially outer end of the eccentric groove. A locking member is movably arranged in the eccentric groove, and the outer contour of the locking member in the eccentric groove region is adapted to the inner contour of the eccentric groove; one end of the locking member close to the cut-in port is a fitting end, and the other end is a limiting end. The thickness of the locking member gradually increases from the fitting end to the limiting end. A boss passing through the movable groove is arranged on the radially outer side of the locking member close to the limiting end, and a locking bolt is connected to the boss; the locking member can be eccentrically rotated inward to tightly fit and clamp the circular tube wing located in the sleeve hole, and the locking bolt can longitudinally adjust the tightness between the circular tube wing and the locking member.

[0008] Based on the above technical solution, the radially inner and outer ends of the limiting end are respectively in contact with the radially inner and outer side walls of the eccentric groove far from the cut-in port.

[0009] Based on the above technical solution, the boss has a "T" shape profile, and the radially inner wall of the boss can slide along the outer side wall of the convex ring in a fitting manner.

[0010] Based on the above technical solution, an outwardly extending tab is provided at the radially outer end of the boss.

[0011] Based on the above technical solution, a threaded hole is provided on the boss, and the threaded hole radially penetrates through the main body structure of the boss and the locking member, and the locking bolt is connected to the threaded hole.

[0012] Based on the above technical solution, a cushion block is provided at the inner end of the locking bolt, and the cushion block is made of an elastic material.

[0013] Based on the above technical solution, a plurality of hollow grooves are provided at the inner end of the cushion block, and the longitudinal profile of the hollow grooves is in a "dry" shape structure.

[0014] Based on the above technical solution, a gasket made of an elastic material is provided on the inner end face of the locking member.

[0015] Based on the above technical solution, anti-slip lines are provided on the inner end face of the gasket.

[0016] Compared with the prior art, the present utility model has at least the following advantages:

[0017] 1. The wing tube connection structure of this utility model eliminates traditional motor mounts, folding parts, and other connecting components, adopting an integrated design that significantly reduces the number of parts, lowers the overall weight and cost. For agricultural drones, reduced weight can improve endurance, while lower costs facilitate market promotion.

[0018] 2. The connection structure adopted in this utility model consists of only a few components, including a sleeve, an eccentric groove, a locking element, and a locking bolt. The structure is simple and compact, occupying little space. This not only facilitates installation and maintenance but also improves the overall aesthetics of the UAV. Through the eccentric locking principle and adjustable design, the locking element can generate a uniform and powerful clamping force on the circular tube wing, ensuring a firm and reliable connection between the wing and the sleeve. Simultaneously, the design of elastic gaskets and anti-slip textures further enhances the stability of the connection, effectively preventing wing swaying and loosening during flight. Attached Figure Description

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

[0020] Figure 1 This is a schematic diagram of the wing tube connection structure of a UAV in one embodiment;

[0021] Figure 2 for Figure 1 A sectional view;

[0022] Figure 3 This is a cross-sectional view of the casing in section 2;

[0023] Figure 4 for Figure 1 Schematic diagram of the central locking component;

[0024] Figure 5 This is a schematic diagram of the gasket structure in another embodiment;

[0025] Figure 6 This is a schematic diagram of the locking element in another embodiment;

[0026] Figure 7 This is a cross-sectional view of the locking bolt in one embodiment;

[0027] Figure 8 This is a schematic diagram of the pad block in another embodiment;

[0028] Figure 9 for Figure 8 A sectional view.

[0029] The diagram is labeled as follows: 100, sleeve; 110, sleeve hole; 120, convex ring; 121, movable groove; 130, eccentric groove; 131, cutting entrance; 200, locking element; 201, mating end; 202, limiting end; 203, boss; 204, paddle; 205, threaded hole; 206, gasket; 207, anti-slip texture; 208, rope hole; 300, locking bolt; 310, pad; 311, hollow groove. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model. Therefore, the following detailed description of the embodiments of this utility model provided in the accompanying drawings is not intended to limit the scope of the claimed utility model, but merely to represent selected embodiments of this utility model.

[0031] In the description of this utility model, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0032] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0033] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0034] Example 1: Combination Figures 1 to 4 This embodiment discloses a drone wing tube connection structure, which aims to solve the problems of structural wear, complex assembly, and poor stability of existing drone wing connection structures during storage.

[0035] The UAV wing tube connection structure in this embodiment specifically includes a sleeve 100, which is one of the core components of this utility model. The sleeve 100 has a sleeve hole 110 with an axial through hole structure. The size and shape of the sleeve hole 110 are adapted to the circular tube wing of the UAV for insertion and connection. In use, one end of the sleeve hole 110 is fitted onto the wing connected to the main body of the UAV, and the other end is fitted onto the wing connected to the rotor. The two ends of the wing are simultaneously inserted and connected towards the axial center of the sleeve 100.

[0036] The outer wall of the sleeve 100 is provided with a ring-shaped protrusion 120, which serves to support and position the locking member 200.

[0037] Furthermore, such as Figure 3 As shown, the sleeve 100 has an eccentric groove 130 in the inner region of the convex ring 120. The longitudinal profile of the eccentric groove 130 is a "C" shaped structure, and the inner end of the eccentric groove 130 is a cutting entrance 131 that connects to the sleeve hole 110. The cutting entrance 131 allows one end of the eccentric groove 130 to smoothly connect with the inner wall of the sleeve hole 110, thus forming a smooth guiding structure.

[0038] Combination Figures 1 to 3 The convex ring 120 has a movable groove 121 with a radial through-hole structure. The radially inner end of the movable groove 121 communicates with the radially outer end of the eccentric groove 130. A locking member 200 is movably disposed within the eccentric groove 130. The outer contour of the locking member 200 in the region of the eccentric groove 130 matches the inner contour of the eccentric groove 130 to ensure that the locking member 200 can rotate smoothly within the eccentric groove 130 without wobbling. The eccentric groove 130 provides a track for the installation and movement of the locking member 200. Due to its eccentric design, when the locking member 200 rotates within the eccentric groove 130, it can generate centripetal or centrifugal displacement, thereby achieving the clamping or loosening of the circular tube airfoil. The movable groove 121 provides a movement channel for the boss 203 on the locking member 200, allowing the locking bolt 300 to longitudinally adjust the locking member 200 through the boss 203.

[0039] Specifically, in combination Figure 2 and Figure 4 As shown, the locking member 200 has a fitting end 201 near the inlet 131 and a limiting end 202 at the other end. The thickness of the locking member 200 gradually increases from the fitting end 201 to the limiting end 202. This gradual thickness design is key to achieving eccentric internal rotation clamping. The inner and outer radial ends of the limiting end 202 are respectively fitted to the inner and outer radial walls of the eccentric groove 130 away from the inlet 131. This ensures that the locking member 200 maintains a stable path when sliding within the eccentric groove 130.

[0040] A boss 203 passing through the movable groove 121 is provided radially outward on the side of the locking member 200 near the limiting end 202, and a locking bolt 300 is connected to the boss 203. The locking member 200 can be eccentrically rotated inward to fit and tighten the circular tube wing located in the sleeve hole 110, and the locking bolt 300 can be longitudinally adjusted between the circular tube wing and the locking member 200. When the locking member 200 is eccentrically rotated inward in the eccentric groove 130, as its thickness gradually increases, the fitting end 201 will gradually approach the circular tube wing, eventually achieving a tight fit and tightening of the wing, thereby firmly fixing the wing in the sleeve 100. The limiting end 202 serves to limit the rotation angle of the locking member 200, ensuring that the locking member 200 moves within a predetermined range. The cooperation between the boss 203 and the locking bolt 300 enables longitudinal adjustment of the locking member 200, further enhancing the stability of the connection.

[0041] Furthermore, in order to make the movement path of the locking member 200 more stable, the boss 203 has a "T" shaped profile, and the radial inner wall of the boss 203 can slide along the outer wall of the convex ring 120. This makes there a radial limiting structure between the locking member 200 and the convex ring 120, preventing the locking member 200 from wobbling radially during the sliding process, which would cause instability of the disconnected structure.

[0042] To make the control of the locking member 200 more convenient and efficient, the outer radial end of the boss 203 is provided with an outwardly extending paddle 204 for the operator to control the locking member 200 by paddle.

[0043] like Figure 2 As shown, the boss 203 is provided with a threaded hole 205, which radially penetrates the main structure of the boss 203 and the locking member 200. The locking bolt 300 is connected to the threaded hole 205. This structure allows the inner end of the screw of the locking bolt 300 to abut against and apply pressure to the surface of the internal circular tube wing after tightening, further improving the locking effect.

[0044] When using the UAV wing tube connection structure of this utility model, first insert the UAV's cylindrical wing tube into the sleeve hole 110 of the sleeve 100. Then, rotate the locking member 200 so that it rotates eccentrically inward within the eccentric groove 130. As the locking member 200 rotates, its contact end 201 gradually approaches the cylindrical wing tube. Due to the gradual increase in thickness of the locking member 200, a centripetal clamping force is generated on the wing, firmly fixing the wing inside the sleeve 100. Tighten the locking bolt 300 to further achieve a secure locking connection. When it is necessary to store the UAV, loosen the locking bolt 300 and reverse it so that the locking member 200 rotates eccentrically outward within the eccentric groove 130, releasing the clamping constraint on the wing, and the wing can be easily pulled out for storage and organization.

[0045] Example 2: Based on Example 1, combined with Figure 5 As shown in the figure, in this embodiment, a gasket 206 made of an elastic material (such as rubber, etc.) is provided on the inner end surface of the locking member 200, and an anti-slip pattern 207 is provided on the inner end surface of the gasket 206. The gasket 206 can increase the contact area between the locking member 200 and the circular tube wing, disperse the pressure, and avoid wing deformation caused by excessive local pressure. The anti-slip pattern 207 further enhances the friction between the gasket 206 and the wing, prevents the wing from loosening due to vibration during flight, and improves the reliability of the connection.

[0046] Embodiment 3: On the basis of Embodiment 1, combined with Figure 6 As shown in the figure, in this embodiment, in order to make the operation mode of the locking member 200 more diverse and labor-saving, a rope hole 208 with a transverse through-hole structure is provided on the side wall of the dial 204. The rope hole 208 can be used to thread a connecting pull rope. During the locking operation, the eccentric inner rotation movement control of the locking member 200 can be realized by pulling the pull rope. This method is more convenient and labor-saving.

[0047] Embodiment 4: On the basis of Embodiment 1, combined with Figure 7 As shown in the figure, in this embodiment, a cushion block 310 is provided at the inner end of the locking bolt 300. The cushion block 310 is made of an elastic material (such as rubber, etc.). This structure enables the locking bolt 300 to have a certain elastic space when extruding and pressing the wing, which not only improves the anti-slip effect, but also can reduce the rigid contact with the wing surface by means of elastic pressing, thereby protecting the surface structure of the wing from wear.

[0048] Embodiment 5: On the basis of Embodiment 4, combined with Figure 8 and Figure 9 As shown in the figure, in this embodiment, a plurality of hollow grooves 311 are provided at the inner end of the cushion block 310. The longitudinal profile of the hollow groove 311 is in the shape of a "dry" character structure. The design of the hollow groove 311 increases the elastic deformation ability of the cushion block 310, enables it to better adapt to different pressure changes, and improves the locking effect. The structure of the hollow groove 311 makes the inner end of the cushion block 310 more flexible and the deformation ability is improved, and it can be appropriately deformed according to the actual situation during the abutting and pressing process to improve the locking effect.

[0049] In summary, the wing tube connection structure of the present utility model has the advantages of simple structure, convenient assembly, high stability, good reliability, etc., can effectively solve the problems existing in the existing wing tube connection structure of the unmanned aerial vehicle, and has a broad market application prospect.

[0050] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A wing tube connection structure for an unmanned aerial vehicle (UAV), characterized in that, It includes a sleeve (100). The sleeve (100) is provided with a sleeve hole (110) having an axial through-hole structure. The sleeve hole (110) is for inserting and connecting the circular tube wing of the unmanned aerial vehicle. A convex ring (120) with an annular structure is provided on the outer side wall of the sleeve (100). An eccentric groove (130) is provided in the inner region of the sleeve (100) where the convex ring (120) is located. The longitudinal profile of the eccentric groove (130) is in a "C" shape structure, and the inner end of the eccentric groove (130) is a cut-in port (131) communicating with the sleeve hole (110). An activity groove (121) with a radial through-hole structure is provided on the convex ring (120). The radial inner end of the activity groove (121) is communicated with the radial outer end of the eccentric groove (130). A locking member (200) is movably arranged in the eccentric groove (130). The outer contour of the locking member (200) in the region of the eccentric groove (130) is adapted to the inner contour of the eccentric groove (130); one end of the locking member (200) close to the cut-in port (131) is a fitting end (201), and the other end is a limiting end (202). The thickness of the locking member (200) gradually increases from the fitting end (201) to the limiting end (202). A convex platform (203) passing through the activity groove (121) is arranged on the radial outer side of the locking member (200) close to the limiting end (202). A locking bolt (300) is connected to the convex platform (203); the locking member (200) can be eccentrically rotated inward to fit and tighten the circular tube wing located in the sleeve hole (110), and the locking bolt (300) can longitudinally adjust the tightness between the circular tube wing and the locking member (200).

2. The UAV wing tube connection structure according to claim 1, characterized in that, The radial inner and outer ends of the limiting end (202) are respectively in contact with the radial inner and outer side walls of the eccentric groove (130) on the side away from the cut-in port (131).

3. The UAV wing tube connection structure according to claim 1, characterized in that, The convex platform (203) has a "T" shape profile, and the radial inner wall of the convex platform (203) can slide along the outer side wall of the convex ring (120) in a fitting manner.

4. The UAV wing tube connection structure according to claim 3, characterized in that, An outwardly extending dial (204) is provided at the radial outer end of the convex platform (203).

5. The UAV wing tube connection structure according to claim 1, characterized in that, A threaded hole (205) is provided on the convex platform (203). The threaded hole (205) radially penetrates through the main body structure of the convex platform (203) and the locking member (200), and the locking bolt (300) is connected to the threaded hole (205).

6. The UAV wing tube connection structure according to claim 5, characterized in that, A cushion block (310) is provided at the inner end of the locking bolt (300), and the cushion block (310) is made of an elastic material.

7. The UAV wing tube connection structure according to claim 6, characterized in that, A number of hollow grooves (311) are provided at the inner end of the cushion block (310), and the longitudinal profile of the hollow grooves (311) is in a "dry" shape structure.

8. The UAV wing tube connection structure according to claim 1, characterized in that, A gasket (206) made of an elastic material is provided on the inner end surface of the locking member (200).

9. The UAV wing tube connection structure according to claim 8, characterized in that, Anti-slip lines (207) are provided on the inner end surface of the gasket (206).

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