Unmanned aerial vehicle paddle structure capable of being quickly disassembled and assembled

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle paddle structure capable of being quickly disassembled and assembled. The unmanned aerial vehicle paddle structure comprises a paddle body, a base assembly and a cover plate assembly, and the paddle body is located between the base assembly and the cover plate assembly; wherein an inserting hole is formed in the paddle body, a connecting column is arranged at one end of the base assembly, a first external thread is arranged on the connecting column, the cover plate assembly comprises a locking handle, and an internal thread matched with the first external thread is arranged at one end of the locking handle; during assembly, the locking handle is connected with the connecting column penetrating through the inserting hole through rotation of the internal thread and the first external thread, and the blade body is pressed tightly. The unmanned aerial vehicle paddle can be quickly disassembled and assembled, the maintenance efficiency is improved, and the safety and stability in the flight process are guaranteed.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a propeller structure of an unmanned aerial vehicle that can be quickly disassembled and assembled. Background Art

[0002] With the rapid development of drone technology, drones have been widely used in many fields such as aerial photography, agriculture, and rescue. Among them, drone blades are key components, and their performance and ease of maintenance directly affect the user experience of drones. Traditional drone blades are usually fixed with screws or other permanent connections, which makes the disassembly and assembly process cumbersome and time-consuming when the blades are damaged or need maintenance.

[0003] Although the existing UAV propeller connection methods meet flight requirements to a certain extent, they still have obvious shortcomings in terms of quick disassembly and assembly. For example, the screw connection method requires the use of tools during the disassembly and assembly process, and the operation is complicated; while the permanent connection method makes it difficult to replace the propeller blade once it is damaged. These problems limit the efficient maintenance and flight safety of UAVs. Utility Model Content

[0004] In order to solve or partially solve the problems existing in the above-mentioned related technologies, the present application provides a UAV blade structure that can be quickly disassembled and assembled, which can quickly disassemble and assemble the UAV blades, improve maintenance efficiency, and ensure safety and stability during flight.

[0005] In the first aspect, the embodiment of the present application provides a drone blade structure that can be quickly disassembled and assembled, using the following technical solution:

[0006] A quickly disassembled drone blade structure comprises: a blade body, a base assembly and a cover assembly, wherein the blade body is located between the base assembly and the cover assembly; wherein a plug hole is provided on the blade body, a connecting column is provided at one end of the base assembly, and a first external thread is provided on the connecting column, and the cover assembly comprises a locking handle, and an internal thread adapted to the first external thread is provided at one end of the locking handle; during assembly, the locking handle is connected to the connecting column passing through the plug hole and presses the blade body through the rotation of the internal thread and the first external thread.

[0007] By adopting the above technical solution, the internal thread of the locking handle can be manually twisted to tightly match the first external thread on the connecting column, thereby firmly fixing the blade body between the base assembly and the cover assembly. This connection method is simple and efficient, does not require the use of additional tools, greatly improves the efficiency of disassembly and assembly of the blade, and further improves the maintenance efficiency to ensure safety and stability during flight.

[0008] Optionally, the base assembly includes: a driving member, a base and a first fixing member, the base is located between the driving member and the blade body, the connecting column is located at an end of the base away from the driving member, the output end of the driving member and the base are correspondingly provided with a first fixing hole, and the base is connected to the output end of the driving member through the first fixing member passing through the first fixing hole.

[0009] By adopting the above technical solution, the output end of the driving member is connected to the first fixing hole via the first fixing member to fix the base, thereby ensuring the connection stability of the base assembly.

[0010] Optionally, the base assembly further includes a second fixing member, and a second fixing hole is provided on the blade body and the base corresponding to the second fixing member.

[0011] By adopting the above technical solution, the blade body can be mounted on the second fixing part through the second fixing hole. During assembly, the base assembly first limits the blade body through the second fixing part to facilitate the locking handle connection to the connecting column, while ensuring the structural stability of the driving part and the blade body.

[0012] Optionally, the cover plate assembly further includes: a pressure plate, which is sleeved on the locking handle and located between the locking handle and the blade body.

[0013] By adopting the above technical solution, providing a pressure plate can further increase the pressing force of the locking handle on the blade body, making the connection more secure.

[0014] Optionally, a limiting hole is provided on the pressing plate corresponding to the second fixing member.

[0015] By adopting the above technical solution, the limiting hole cooperates with the second fixing member to ensure the accurate positioning of the pressure plate during the locking process, prevent the pressure plate from being offset or rotated, and thus enhance the stability of the blade structure.

[0016] Optionally, the cover plate assembly further includes: an anti-loosening member, which is sleeved on the locking handle and located between the locking handle and the pressure plate.

[0017] By adopting the above technical solution, the anti-loosening member can effectively prevent the locking handle from loosening after long-term use, further improving the safety and reliability of the blade structure.

[0018] Optionally, the number of the second fixing member, the second fixing hole and the limiting hole is four respectively.

[0019] By adopting the above technical solution, the four second fixing members, the second fixing holes and the limiting holes can make the connection between the blade body and the base more uniform and stable, and effectively avoid the problems of stress concentration and local looseness.

[0020] Optionally, a second external thread is further provided at one end of the locking handle, and the pressing plate is rotatably fixed to the locking handle via the second external thread.

[0021] By adopting the above technical solution, a second external thread is further provided on the locking handle, and the pressure plate is rotatably fixed on the locking handle through the second external thread. This connection method is not only convenient for disassembly and assembly, but also ensures a close fit between the pressure plate and the locking handle, further improving the stability of the blade structure.

[0022] In summary, the present application includes at least one of the following beneficial technical effects:

[0023] 1. The internal thread of the locking handle can be manually twisted to tightly fit with the first external thread on the connecting column, thereby firmly fixing the propeller body between the base assembly and the cover assembly. This connection method is simple and efficient, and does not require the use of additional tools. It greatly improves the efficiency of disassembly and assembly of the propeller blades, thereby improving maintenance efficiency to ensure safety and stability during flight;

[0024] 2. The output end of the driving member is connected to the first fixing hole through the first fixing member to fix the base, thereby ensuring the connection stability of the base assembly;

[0025] 3. The blade body can be sleeved on the second fixing member through the second fixing hole, so that during assembly, the base assembly first limits the blade body through the second fixing member to facilitate the locking handle connection to the connecting column, while ensuring that the driving member can synchronously drive the blade body to rotate;

[0026] 4. The limiting hole cooperates with the second fixing member to ensure the accurate positioning of the pressure plate during the locking process, prevent the pressure plate from deflecting or rotating, and thus enhance the overall stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of a rapidly disassembled UAV blade structure disclosed in an embodiment of the present application;

[0028] Figure 2 for Figure 1 A schematic diagram of the exploded structure of a UAV blade structure that can be quickly disassembled and assembled is shown;

[0029] Figure 3 for Figure 1 A schematic diagram of a partially exploded structure of a UAV blade structure that can be quickly disassembled and assembled is shown;

[0030] Figure 4 for Figure 1 A partial cross-sectional view of a UAV blade structure that can be quickly disassembled and assembled is shown.

[0031] Description of reference numerals:

[0032] 10. Blade body; 11. Plug-in hole; 12. Second fixing hole; 20. Base assembly; 21. Connecting column; 211. First external thread; 22. Driving member; 23. Base; 24. First fixing member; 25. First fixing hole; 26. Second fixing member; 30. Cover assembly; 31. Locking handle; 311. Second external thread; 32. Press plate; 321. Limiting hole; 33. Anti-loosening member. DETAILED DESCRIPTION

[0033] The terms used in the following embodiments of the present application are only for the purpose of describing specific embodiments, and are not intended to be used as limitations to the present application. As used in the specification and appended claims of the present application, the singular expressions "one", "a kind of", "above", "the" and "this" are intended to also include plural expressions, unless there is a clear indication to the contrary in the context. It should also be understood that the term "and / or" used in the present application refers to and includes any or all possible combinations of one or more listed items.

[0034] In the following, the terms "first" and "second" are used for descriptive purposes only and are not to be understood as suggesting or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features, and in the description of the embodiments of the present application, unless otherwise specified, "plurality" means two or more.

[0035] The technical solution of the embodiments of the present application is described in detail below with reference to the accompanying drawings.

[0036] See also Figure 1 , is a rapidly disassembled drone blade structure disclosed in an embodiment of the present application, comprising: a blade body 10, a base assembly 20 and a cover assembly 30, wherein the blade body 10 is located between the base assembly 20 and the cover assembly 30;

[0037] See also Figure 2 The blade body 10 is provided with a plug hole 11 located in the middle of the blade body 10. One end of the base assembly 20 is provided with a connecting column 21 for penetrating the plug hole 11, and the connecting column 21 is provided with a first external thread 211.

[0038] The cover assembly 30 includes a locking handle 31, and an internal thread (not marked in the figure) adapted to the first external thread 211 is provided at one end of the locking handle 31. During assembly, the connecting column 21 of the base assembly 20 is first inserted through the plug hole 11, so that the user can manually screw the locking handle 31 to connect to the connecting column 21 based on the rotational connection between the internal thread and the first external thread 211, thereby pressing the blade body 10 to achieve assembly of the blade body 10, the base assembly 20 and the cover assembly 30.

[0039] See also Figure 2 and Figure 3 The seat assembly includes a driving member 22, a base 23, a first fixing member 24 and a second fixing member 26. The connecting column 21 is located at the end of the base 23 away from the driving member 22, so as to penetrate the plug-in member and connect the locking handle 31. The driving member 22 is a motor, and the output end of the driving member 22, i.e., the rotating end, and the base 23 are correspondingly provided with a first fixing hole 25, so that the first fixing member 24 penetrates the first fixing hole 25 to achieve a stable connection between the driving member 22 and the base 23.

[0040] See also Figure 2 A second fixing hole 12 is provided on the blade body 10 and the base 23 corresponding to the second fixing piece 26. The second fixing piece 26 and the second fixing hole 12 are correspondingly set to four and are evenly arranged, so that the connection between the blade body 10 and the base 23 can be more uniform and stable, and the problems of stress concentration and local looseness can be effectively avoided.

[0041] Thus, the blade body 10 can be sleeved on the second fixing member 26 through the second fixing hole 12. During assembly, the base assembly 20 first limits the blade body 10 through the second fixing member 26, so as to facilitate the locking handle 31 to connect the connecting column 21, while ensuring the structural stability of the driving member 22 and the blade body 10.

[0042] The cover plate assembly 30 further includes a pressing plate 32 , which is used to be sleeved on the locking handle 31 and is located between the locking handle 31 and the blade body 10 .

[0043] Among them, a through hole is set in the middle of the pressure plate 32, or an internal spiral is set based on the thickness of the pressure plate 32, and a corresponding second external thread 311 is set on the outer side of one end of the locking handle 31. The pressure plate 32 can be screwed on the locking handle 31 in a rotational manner, so that when the locking handle 31 is screwed by external force, the pressure plate 32 synchronously presses the blade body 10, thereby increasing the clamping force of the locking handle 31 on the blade body 10, making the overall connection more secure.

[0044] The pressing plate 32 is further provided with limiting holes 321 , which correspond to the second fixing members 26 , and are each provided with four limiting holes, for example.

[0045] The limiting hole 321 cooperates with the second fixing member 26 to ensure accurate positioning of the pressing plate 32 during the locking process, and prevent the pressing plate 32 from being offset or rotated, thereby enhancing the stability of the blade structure.

[0046] In addition, the cover plate assembly 30 further includes an anti-loosening member 33 which is sleeved on one end of the locking handle 31 and is located between the locking handle 31 and the pressing plate 32 .

[0047] Among them, a through hole is provided in the middle of the anti-loosening part 33, and anti-slip grooves are provided on the two side surfaces relative to the locking handle 31 and the pressure plate 32, so as to increase the friction resistance between the side surfaces, so as to effectively prevent the locking handle 31 from loosening after long-term use, and further improve the safety and reliability of the blade structure.

[0048] In summary, the embodiment of the present application discloses a rapidly disassembled drone blade structure, which can be firmly fixed between the base assembly 20 and the cover assembly 30 by manually twisting the locking handle 31 so that the internal thread thereof is tightly matched with the first external thread 211 on the connecting column 21. This connection method is simple and efficient, does not require the use of additional tools, greatly improves the efficiency of disassembly and assembly of the blade, and further improves the maintenance efficiency, and can ensure safety and stability during flight.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A UAV blade structure that can be quickly disassembled and assembled, characterized in that: include: A blade body (10), a base assembly (20) and a cover assembly (30), wherein the blade body (10) is located between the base assembly (20) and the cover assembly (30); The blade body (10) is provided with a plug hole (11), one end of the base assembly (20) is provided with a connecting column (21), and the connecting column (21) is provided with a first external thread (211), and the cover assembly (30) includes a locking handle (31), and one end of the locking handle (31) is provided with an internal thread adapted to the first external thread (211); during assembly, the locking handle (31) is connected to the connecting column (21) passing through the plug hole (11) by rotating the internal thread and the first external thread (211), and the blade body (10) is pressed.

2. The rapidly detachable UAV blade structure according to claim 1, characterized in that: The base assembly (20) comprises: a driving member (22), a base (23) and a first fixing member (24); the base (23) is located between the driving member (22) and the blade body (10); the connecting column (21) is located at an end of the base (23) away from the driving member (22); a first fixing hole (25) is correspondingly provided on the output end of the driving member (22) and the base (23); the base (23) is connected to the output end of the driving member (22) via the first fixing member (24) penetrating the first fixing hole (25).

3. The rapidly detachable UAV blade structure according to claim 2, characterized in that: The base assembly (20) further comprises a second fixing member (26), and a second fixing hole (12) is provided on the blade body (10) and the base (23) corresponding to the second fixing member (26).

4. The rapidly detachable UAV blade structure according to claim 3 is characterized in that: The cover plate assembly (30) further comprises: a pressure plate (32) sleeved on the locking handle (31) and located between the locking handle (31) and the blade body (10).

5. The rapidly detachable UAV blade structure according to claim 4, characterized in that: A limiting hole (321) is provided on the pressing plate (32) corresponding to the second fixing member (26).

6. The rapidly detachable UAV blade structure according to claim 4, characterized in that: The cover plate assembly (30) further comprises: an anti-loosening member (33) sleeved on the locking handle (31) and located between the locking handle (31) and the pressing plate (32).

7. The rapidly detachable UAV blade structure according to claim 5, characterized in that: The second fixing member (26), the second fixing hole (12) and the limiting hole (321) are respectively arranged in four numbers.

8. The rapidly detachable UAV blade structure according to claim 5, characterized in that: One end of the locking handle (31) is further provided with a second external thread (311), and the pressing plate (32) is rotatably fixed on the locking handle (31) via the second external thread (311).

Images