Unmanned aerial vehicle paddle structure

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. An unmanned aerial vehicle paddle structure comprises a paddle body, a base assembly, a cover plate assembly and an unlocking pin. During installation, the paddle body is installed on the base assembly, the cover plate assembly penetrates through the paddle body and is clamped with the base assembly, and the paddle body is fixedly installed on the base assembly. During disassembly, an unlocking hole is formed in the cover plate assembly, the unlocking pin is matched with the unlocking hole, the cover plate assembly is separated from the base assembly, and the paddle body is rapidly disassembled. According to the unmanned aerial vehicle paddle structure, rapid and stable disassembly and assembly can be achieved, and the maintenance efficiency and the flight stability of the unmanned aerial vehicle paddle are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and in particular to a blade 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, agricultural spraying, etc. The propeller blade of a drone is an extremely important part of the entire drone, but it is also a part that is easily damaged and often needs to be replaced and maintained.

[0003] Traditional drone blades are usually installed by permanent connection or screw fixing. The permanent connection method cannot replace the blades once damaged, and the screw fixing method requires additional installation tools during the disassembly and assembly process, which cannot be quickly disassembled and assembled, resulting in limited efficient maintenance and flight safety of the drone to a certain extent. Utility Model Content

[0004] In order to solve the above-mentioned technical problems, the utility model provides a UAV blade structure.

[0005] The present application provides a drone blade structure, which adopts the following technical solution:

[0006] A UAV blade structure, comprising:

[0007] The blade body, base assembly, cover assembly, and unlocking pin;

[0008] The blade body is mounted on the base assembly, and the cover assembly penetrates the blade body and engages with the base assembly to fix the blade body on the base assembly;

[0009] The cover plate assembly is provided with an unlocking hole, and the unlocking pin cooperates with the unlocking hole to separate the cover plate assembly from the base assembly, thereby realizing rapid disassembly of the blade body.

[0010] By adopting the above technical solution, the stable installation and convenient disassembly of the blade body are achieved through the mutual cooperation of the base assembly, the cover assembly and the unlocking pin structure.

[0011] Optionally, the base assembly includes a base and a driving member, the base is provided with a first fixing hole and a first fixing member, and the first fixing member passes through the first fixing hole to fix the base on the driving member.

[0012] By adopting the technical solution, the base and the driving member are tightly combined by utilizing the first fixing hole and the first fixing member, thereby ensuring that the base is firmly fixed on the driving member, enhancing the stability of the structure, and ensuring the stability of the base when disassembling and assembling the drone blades.

[0013] Optionally, the base is also provided with a second fixing piece and a pin hole, and the second fixing piece is arranged around the pin hole; the blade body is provided with a second fixing hole corresponding to the second fixing piece and an insertion hole corresponding to the pin hole; the second fixing piece and the second fixing hole are interlocked to fix the blade body to the base.

[0014] By adopting the above technical solution, the second fixing piece of the base is engaged with the second fixing hole of the blade body, thereby achieving a stable connection between the blade body and the base and improving the accuracy and convenience of installation.

[0015] Optionally, the base is further provided with a third fixing hole for fixing the cover plate assembly.

[0016] By adopting the above technical solution, the third fixing hole can install and fix the cover plate assembly on the blade body.

[0017] Optionally, the base assembly further includes a positioning pin, an elastic device and a third fixing member, the elastic device is arranged between the positioning pin and the third fixing member, the positioning pin, the elastic device and the third fixing member cooperate with each other, pass through the third fixing hole to engage and fix the cover assembly.

[0018] By adopting the above technical solution, when the cover assembly is installed, the positioning pins are used to ensure precise positioning, the elastic device provides adaptive pre-tightening, and the third fixing member is firmly locked. The three cooperate with each other to penetrate the third fixing hole, thereby achieving elastic and efficient installation of the cover assembly, simplifying the installation steps and enhancing the stability of the connection, thereby improving the maintenance efficiency of the UAV blade structure.

[0019] Optionally, the cover plate assembly includes a fourth fixing member, a positioning pin, and a pressure plate, wherein a fourth fixing hole is provided on the pressure plate, the positioning pin is installed on the pressure plate through the fourth fixing member, and the positioning pin is used to pass through the plug hole and be fixed in the pin hole.

[0020] By adopting the above technical solution, the structural stability of the cover plate assembly is improved, the structural strength of the cover plate assembly is ensured during disassembly and assembly, the service life is increased, and the stable strength of the cover plate assembly after installation is guaranteed.

[0021] Optionally, the cover plate assembly is further provided with an adjusting gasket, which is arranged below the pressure plate and between the pressure plate and the blade body, and is used to reduce friction between the pressure plate and the blade body.

[0022] By adopting the above technical solution, the gasket is adjusted to reduce the friction between the pressure plate and the blade body, improve assembly accuracy and operating stability, extend the service life of components, and facilitate disassembly.

[0023] Optionally, a positioning hole matched with the positioning pin is provided at one end of the positioning pin shaft, and the positioning hole is used for mutual engagement and fixation with the base assembly.

[0024] By adopting the above technical solution, the positioning hole at the end of the positioning pin shaft is precisely engaged with the positioning pin of the base assembly, thereby achieving a stable connection between the cover assembly and the base assembly, enhancing the overall stability of the structure, improving the assembly accuracy, and improving the disassembly and assembly efficiency of the UAV blades.

[0025] Optionally, when the positioning pin shaft is assembled, the positioning pin is squeezed around through the plug hole and the pin hole; after the positioning pin shaft is assembled in place, the positioning pin rebounds under the action of the elastic device and is engaged and fixed with the positioning hole to achieve the installation and fixation of the blade body.

[0026] By adopting the above technical solution, during the assembly process, the locating pin passes through the plug hole and the pin hole, and the locating pin is squeezed in the pin hole of the base to expand around at the same time. At this time, the locating pin is easy to install into the base. When the locating pin is installed in place, the locating pin rebounds quickly under the drive of the elastic device and is accurately inserted into the locating hole of the locating pin, thereby achieving a firm locking of the locating pin, thereby achieving the cover plate assembly to pass through the blade body and be accurately and firmly installed in the base assembly, thereby achieving a firm and fast installation of the UAV blade structure, and improving the installation stability and efficiency of the UAV.

[0027] Optionally, an unlocking hole is further provided on the positioning pin shaft. After the unlocking pin is installed in the unlocking hole, the positioning pin is squeezed outward to disengage from the positioning hole, thereby releasing the engagement and fixation between the cover assembly and the base assembly, thereby realizing rapid disassembly of the blade body.

[0028] By adopting the above technical solution, the unlocking pin is installed into the unlocking hole, and the positioning pin is squeezed to make it disengage from the positioning hole, thereby releasing the fastening state of the cover assembly and the base assembly. The cover assembly and the base assembly can be disassembled, thereby realizing the rapid disassembly of the blade assembly, realizing the rapid and convenient disassembly of the UAV blade structure, and improving the maintenance efficiency of the UAV blade structure.

[0029] In summary, the present application includes at least one of the following beneficial technical effects:

[0030] Based on the above, here are the 3 most critical technical benefits:

[0031] 1. By designing the matching mechanism of the unlocking pin and the unlocking hole, the rapid installation and disassembly of the UAV blades is realized, the disassembly and assembly efficiency is improved, and the blades are quickly replaced or maintained, thereby improving the overall maintainability and flexibility of the UAV.

[0032] 2. By utilizing the precise coordination of the positioning pins, elastic devices, the third fixing parts, and the positioning holes on the positioning pin shaft, a stable connection and high-precision positioning are achieved between the blade body, the base assembly, and the cover assembly, thereby enhancing the overall stability of the blade structure, ensuring the accuracy and reliability of the blade during high-speed rotation, and improving the flight safety performance of the UAV.

[0033] 3. The propeller structure of the drone adopts a modular design, and each component is relatively independent and easy to replace. When the propeller needs to be maintained or replaced, it can be disassembled and assembled through simple operations without disassembling the drone as a whole, which reduces maintenance costs, improves maintenance efficiency, and also extends the service life of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The present invention will be further described below with reference to the accompanying drawings and embodiments, in which:

[0035] Figure 1 It is a structural schematic diagram of a drone blade structure provided in an embodiment of the present application;

[0036] Figure 2 This is a schematic diagram of the exploded structure of a UAV blade structure provided in an embodiment of the present application;

[0037] Figure 3 is a cross-sectional view of a base assembly in a drone blade structure provided by an embodiment of the present application;

[0038] Figure 4 It is a structural diagram of a bottom component and a cover component of a drone blade structure provided in an embodiment of the present application.

[0039] Description of Figure Numbers

[0040] 10. Blade body; 11. Plug-in hole; 12. Second fixing hole; 20. Base assembly; 21. Base; 211. Second fixing piece; 212. Pin hole; 213. First fixing piece; 214. Third fixing hole; 215. First fixing hole; 22. Driving piece; 23. Positioning pin; 24. Elastic device; 25. Third fixing piece; 30. Cover assembly; 31. Fourth fixing piece; 32. Positioning pin shaft; 321. Positioning hole; 322. Unlocking hole; 33. Press plate; 331. Fourth fixing hole; 34. Adjusting gasket; 40. Unlocking pin. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0042] The specific implementation of the present application is described in detail below with reference to the accompanying drawings:

[0043] Example 1

[0044] This embodiment provides a UAV blade structure that can be quickly disassembled and assembled. Figure 1 and Figure 2 As shown, a UAV blade structure that can be quickly disassembled and assembled includes: a blade body 10, a base assembly 20, a cover assembly 30 and an unlocking pin 40.

[0045] Specifically, the blade body 10 is disposed between the base assembly 20 and the cover assembly 30. The blade body 10 is provided with a plug hole 11 and a second fixing hole 12, wherein the plug hole 11 and the positioning pin shaft 32 of the cover assembly 30 are mutually engaged, and the second fixing hole 12 and the second fixing member 211 on the base 21 of the base assembly 20 are mutually engaged, so that the blade body 10 is fixed between the base assembly 20 and the cover assembly 30.

[0046] Specifically, the base assembly 20 includes a base 21, a driving member 22, a positioning pin 23, an elastic device 24 and a third fixing member 25, wherein the base 21 is provided with a first fixing hole 215 and a first fixing member 213, and the base 21 is fixed to the driving member 22 by passing through the first fixing hole 215 through the first fixing member 213. The positioning pin 23, the elastic device 24 and the third fixing member 25 are installed in the third fixing hole 214 on the side of the base 21, and the elastic device 24 is arranged between the positioning pin 23 and the third fixing member 25, and the positioning pin 23, the elastic device 24 and the third fixing member 25 cooperate with each other, and the cover assembly 30 can be fixed by passing through the third fixing hole 214.

[0047] Specifically, the cover assembly 30 includes a fourth fixing member 31, a positioning pin shaft 32, a pressure plate 33 and an adjustment gasket 34. The pressure plate 33 is provided with a fourth fixing hole 331, the positioning pin shaft 32 is installed on the pressure plate 33 through the fourth fixing member 31, and the adjustment gasket 34 is arranged below the pressure plate 33, between the pressure plate 33 and the blade body 10, and is used to reduce the friction between the pressure plate 33 and the blade body 10. In addition, one end of the positioning pin shaft 32 is provided with a plurality of positioning holes 321, which can be mutually adapted with the positioning pin 23 in the base assembly 20. When the positioning pin shaft 32 is installed into the base assembly 20, the positioning pin shaft 32 passes through the plug hole 11 and engages with the positioning pin 23, thereby being fixed in the pin hole 212.

[0048] Example 2

[0049] Based on Example 1, this example provides a partial structural diagram of the UAV blade structure when it is installed. Figure 3 and Figure 4 shown.

[0050] Specifically, Figure 3 The figure shows a cross-sectional view of the base assembly in the UAV blade structure, wherein the driving member adopts a multi-layer structure, and the uppermost layer for installing the base 21 belongs to the output layer, which is used to output a control signal to control the rotation of the blade. When the base 21 is installed on the driving member, the positioning pin, the elastic device and the third fixing member are installed in the third fixing hole 214 in the base 21 for clamping the cover assembly; a second fixing member 211 is also provided at the upper end of the base 21 for installing the blade body 10.

[0051] Specifically, Figure 4 The figure shows a structural diagram of the bottom component and the cover component of the UAV blade structure, wherein when the cover component is installed on the bottom component, the second fixing member 211 will contact the adjustment gasket, the positioning pin shaft in the cover component is installed on the pressure plate, passes through the plug hole 11 and is fixed in the pin hole 212, and the unlocking pin is installed in the positioning pin shaft, which can be used for disassembly and installation.

[0052] Example 3

[0053] Based on Example 1 and Example 2, this embodiment provides a method for disassembling and assembling a drone blade structure.

[0054] When installing the UAV blade structure, first use the four positioning holes 321 on the positioning pin shaft 32 to match the positioning pin 23 in the base assembly 20. The positioning pin shaft 32 passes through the pin hole 212 on the base 21 to squeeze the surrounding positioning pins 23 in all directions. At the same time, the elastic force of the elastic device 24 is used to ensure that the positioning pin 23 can automatically rebound after being installed in place and tightly fit into the positioning hole 321 of the positioning pin shaft 32. This process not only realizes the stable connection between the blade body 10 and the base assembly 20, but also improves the installation efficiency of the UAV blade structure.

[0055] When the drone blade structure is disassembled, the positioning pin shaft 32 is designed with an unlocking hole 322. The unlocking pin 40 is inserted into the unlocking hole 322 and a certain force is applied to squeeze the positioning pin 23 around again to make it disengage from the positioning hole 321, thereby releasing the base assembly 20 from the cover assembly 30. The operation is simple and quick, and no complicated tools or cumbersome steps are required. The blade body 10 can be easily separated from the base assembly 20, which greatly facilitates the replacement and maintenance of the blade. The drone blades can be quickly and stably installed and disassembled, and the maintenance convenience, safety and stability of the drone during use are enhanced.

[0056] The above are all preferred embodiments of the present invention, and the protection scope of the present invention is not limited thereby. Any equivalent replacement and improvement based on the technical essence of the present invention shall be included in the protection scope of the present invention. At the same time, the embodiments of the present invention can be used in combination with each other to produce more different implementation schemes.

Claims

1. A UAV blade structure, characterized in that: include: A blade body (10), a base assembly (20), a cover assembly (30) and an unlocking pin (40); The blade body (10) is mounted on the base assembly (20); the cover assembly (30) passes through the blade body (10) and is engaged with the base assembly (20) to fix the blade body (10) on the base assembly (20); The cover plate assembly (30) is provided with an unlocking hole (322), and the unlocking pin (40) cooperates with the unlocking hole (322) to separate the cover plate assembly (30) from the base assembly (20), thereby realizing rapid disassembly of the blade body (10).

2. The UAV blade structure according to claim 1, characterized in that: The base assembly (20) comprises a base (21) and a driving member (22); a first fixing hole (215) and a first fixing member (213) are provided on the base (21); the first fixing member (213) passes through the first fixing hole (215) to fix the base (21) on the driving member (22).

3. The UAV blade structure according to claim 2, characterized in that: The base (21) is further provided with a second fixing member (211) and a pin hole (212); the second fixing member (211) is arranged around the pin hole (212); the blade body (10) is provided with a second fixing hole (12) corresponding to the second fixing member (211) and a plug-in hole (11) corresponding to the pin hole (212); the second fixing member (211) and the second fixing hole (12) are mutually engaged to fix the blade body (10) on the base (21).

4. The UAV blade structure according to claim 3, characterized in that: The base (21) is also provided with a third fixing hole (214) for fixing the cover plate assembly (30).

5. The UAV blade structure according to claim 4, characterized in that: The base assembly (20) further comprises a positioning pin (23), an elastic device (24) and a third fixing member (25); the elastic device (24) is arranged between the positioning pin (23) and the third fixing member (25); the positioning pin (23), the elastic device (24) and the third fixing member (25) cooperate with each other and penetrate through the third fixing hole (214) to engage and fix the cover assembly (30).

6. The UAV blade structure according to claim 5, characterized in that: The cover plate assembly (30) comprises a fourth fixing member (31), a positioning pin shaft (32), and a pressure plate (33); a fourth fixing hole (331) is provided on the pressure plate (33); the positioning pin shaft (32) is installed on the pressure plate (33) through the fourth fixing member (31); and the positioning pin shaft (32) is used to pass through the plug hole (11) and be fixed in the pin hole (212).

7. The UAV blade structure according to claim 6, characterized in that: The cover plate assembly (30) is also provided with an adjustment gasket (34), which is arranged below the pressure plate (33) and between the pressure plate (33) and the blade body (10) to reduce friction between the pressure plate (33) and the blade body (10).

8. The UAV blade structure according to claim 6, characterized in that: One end of the positioning pin shaft (32) is provided with a positioning hole (321) matched with the positioning pin (23), and the positioning hole (321) is used for mutual engagement and fixation with the base assembly (20).

9. The UAV blade structure according to claim 8, characterized in that: When the positioning pin shaft (32) is assembled, the positioning pin (23) is squeezed in all directions through the plug hole (11) and the pin hole (212); after the positioning pin shaft (32) is assembled in place, the positioning pin (23) rebounds under the action of the elastic device (24) and is engaged and fixed with the positioning hole (321), thereby achieving installation and fixation of the blade body (10).

10. The UAV blade structure according to claim 8, characterized in that: The positioning pin shaft (32) is also provided with an unlocking hole (322). After the unlocking pin (40) is inserted into the unlocking hole (322), the positioning pin (23) is squeezed outward to disengage from the positioning hole (321), thereby releasing the engagement and fixation between the cover plate assembly (30) and the base assembly (20), thereby realizing the rapid disassembly of the blade body (10).

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