Carbon fiber unmanned aerial vehicle part

Abstract

The utility model discloses a carbon fiber unmanned aerial vehicle part and belongs to the technical field of unmanned aerial vehicle parts, the carbon fiber unmanned aerial vehicle part comprises a main body module and four part dismounting and mounting modules, the main body module comprises an unmanned aerial vehicle main body, four mounting blocks are fixedly connected to the surface of the unmanned aerial vehicle main body, and the four part dismounting and mounting modules are arranged on the four mounting blocks correspondingly; and the part dismounting and mounting module comprises a mounting assembly arranged on one of the mounting blocks, a stabilizing assembly is arranged between the mounting assembly and one of the mounting blocks, and a propeller assembly is arranged on the mounting assembly. The mounting assembly can be fixed, the stability of the mounting assembly can be kept, and the strength of the propeller can be enhanced while the weight is reduced through the arrangement of the propeller assembly.

Description

Technical Field

[0001] This application relates to the field of drone component technology, and more specifically, to a carbon fiber drone component. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and their own program control devices, or operated autonomously by an onboard computer, either completely or intermittently. Compared with manned aircraft, UAVs are often more suitable for missions that are too "dull, dirty, or dangerous". UAVs can be divided into military and civilian applications according to their application fields.

[0003] In the existing technology, most drone components are made of plastic materials, which have low strength. As a result, drone components are easily damaged during use, thus affecting the use of the drone. For example, when one of the drone's propellers is damaged, the drone cannot maintain stability during flight, and it is inconvenient to replace the propeller. To address this, we propose a carbon fiber drone component. Utility Model Content

[0004] To address the aforementioned problems, this application provides a carbon fiber drone component, employing the following technical solution:

[0005] A carbon fiber drone component includes a main body module and four parts assembly / disassembly modules. The main body module includes a drone body, and four mounting blocks are fixedly connected to the surface of the drone body. The four parts assembly / disassembly modules are respectively disposed on the four mounting blocks. Each parts assembly / disassembly module includes a mounting component disposed on one of the mounting blocks. A stabilizing component is disposed between the mounting component and one of the mounting blocks. A propeller component is disposed on the mounting component.

[0006] By adopting the above technical solution, it is easy to replace the propeller, while also enhancing the strength of the propeller.

[0007] Furthermore, the mounting assembly includes a circular groove formed on one of the mounting blocks, and a mounting post is movably inserted into the interior of the circular groove.

[0008] By adopting the above technical solution, the mounting column can be installed.

[0009] Furthermore, the stabilizing component includes two fixing plates that are respectively fixedly connected to both sides of one of the mounting blocks. Each of the two fixing plates has a collar rotatably connected to its opposite side. A double-ended threaded pin is movably inserted between the two collars, one of the mounting blocks, and the mounting post.

[0010] By adopting the above technical solution, the installation column can be initially limited.

[0011] Furthermore, the stabilizing component also includes two easy-tightening nuts that are threaded to both ends of the double-ended threaded pin, and the two easy-tightening nuts respectively abut against the two collars.

[0012] By adopting the above technical solution, the mounting column can be fixed.

[0013] Furthermore, the propeller assembly includes a mounting slot formed at the top of the mounting post, a drive motor is fixedly connected inside the mounting slot, and the output end of the drive motor extends to the top of the mounting post.

[0014] By adopting the above technical solution, the drive motor can be installed.

[0015] Furthermore, the propeller assembly also includes a propeller body fixedly connected to the output end of the drive motor.

[0016] By adopting the above technical solution, the propeller body can be driven to rotate.

[0017] Furthermore, the propeller body can be made of carbon fiber.

[0018] By adopting the above technical solutions, the propeller body can possess characteristics such as high rigidity, high tensile strength, low weight, high chemical resistance, high temperature resistance, and low thermal expansion.

[0019] Furthermore, the main module also includes multiple weight-reduction grooves respectively opened inside multiple mounting blocks.

[0020] By adopting the above technical solution, the weight of the mounting block can be reduced.

[0021] In summary, this application includes the following beneficial technical effects:

[0022] (1) By setting the mounting components, the propeller components can be installed and disassembled. By setting the stabilizing components, the mounting components can be fixed and the stability of the mounting components can be maintained. By setting the propeller components, the strength of the propeller can be increased while reducing the weight.

[0023] (2) The mounting post can be installed by setting the circular groove, the stability of the double-ended threaded pin can be improved by setting the collar and fixing plate, and the double-ended threaded pin can be fixed by setting the easy-tight nut, thereby fixing the mounting post.

[0024] (3) By setting the material of the propeller body to carbon fiber, the propeller body can have the characteristics of high rigidity, high tensile strength, low weight, high chemical resistance, high temperature resistance and low thermal expansion. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the overall structure of this application;

[0026] Figure 2 This is a schematic diagram of a partial explosion structure in this application;

[0027] Figure 3 This is an exploded structural diagram of the parts assembly / disassembly module of this application.

[0028] Explanation of the labels in the diagram:

[0029] 100. Main module; 110. UAV body; 120. Mounting block; 130. Weight reduction slot;

[0030] 200. Parts assembly / disassembly module; 210. Mounting assembly; 211. Circular groove; 212. Mounting post; 220. Stabilizing assembly; 221. Fixing plate; 222. Collar; 223. Double-ended threaded pin; 224. Easy-tightening nut; 230. Propeller assembly; 231. Mounting slot; 232. Drive motor; 233. Propeller body. Detailed Implementation

[0031] The technical solutions in 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. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0032] In the description of this application, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and 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 of this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0033] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" 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 a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0034] The following is in conjunction with the appendix Figure 1-3 This application will be described in further detail.

[0035] Please see Figure 1-3 A carbon fiber drone component includes a main body module 100 and four component assembly / disassembly modules 200. The main body module 100 includes a drone body 110, and four mounting blocks 120 are fixedly connected to the surface of the drone body 110. The four component assembly / disassembly modules 200 are respectively disposed on the four mounting blocks 120. Each component assembly / disassembly module 200 includes a mounting component 210 disposed on one of the mounting blocks 120. A stabilizing component 220 is disposed between the mounting component 210 and one of the mounting blocks 120. A propeller component 230 is disposed on the mounting component 210.

[0036] By setting the mounting component 210, the propeller assembly 230 can be installed. By setting the stabilizing component 220, the mounting component 210 can be fixed and its stability maintained. By setting the propeller assembly 230, the strength of the propeller can be increased while reducing its weight.

[0037] Mounting component 210 includes a circular groove 211 formed on one of the mounting blocks 120, and a mounting post 212 is movably inserted into the groove 211. Stabilizing component 220 includes two fixing plates 221 respectively fixedly connected to both sides of one of the mounting blocks 120. Each of the opposite sides of the two fixing plates 221 is rotatably connected to a collar 222. A double-ended threaded pin 223 is movably inserted between the two collars 222, one of the mounting blocks 120 and the mounting post 212. Stabilizing component 220 also includes two easy-tightening nuts 224 respectively threaded to both ends of the double-ended threaded pin 223, and the two easy-tightening nuts 224 respectively abut against the two collars 222.

[0038] By inserting the mounting post 212 into the inside of the circular groove 211, and then movably inserting the double-ended threaded pin 223 between the two collars 222, one of the mounting blocks 120 and the mounting post 212, and then rotating the easy-tight nut 224 to both ends of the double-ended threaded pin 223, the double-ended threaded pin 223 can be fixed, thereby fixing the mounting post 212, thus realizing the installation and fixing of the propeller assembly 230.

[0039] The propeller assembly 230 includes a mounting groove 231 formed on the top of the mounting post 212. A drive motor 232 is fixedly connected inside the mounting groove 231, and the output end of the drive motor 232 extends to the top of the mounting post 212. The propeller assembly 230 also includes a propeller body 233 fixedly connected to the output end of the drive motor 232. The propeller body 233 may be made of carbon fiber. The main body module 100 also includes a plurality of weight reduction grooves 130 formed inside a plurality of mounting blocks 120.

[0040] By setting the drive motor 232, the propeller body 233 can be driven to rotate. By setting the material of the propeller body 233 as carbon fiber, the propeller body 233 can have the characteristics of high rigidity, high tensile strength, low weight, high chemical resistance, high temperature resistance and low thermal expansion. By setting the weight reduction groove 130, the weight of the mounting block 120 can be reduced.

[0041] The implementation principle of this application embodiment is as follows: When the propeller body 233 needs to be replaced, firstly rotate the two easy-tightening nuts 224 so that the two easy-tightening nuts 224 can be removed from both ends of the double-ended threaded pin 223, thereby releasing the fixation of the double-ended threaded pin 223. Then, pull out the double-ended threaded pin 223 so that the double-ended threaded pin 223 can be removed from the interior of the two collars 222, one of the mounting blocks 120 and the mounting post 212, thereby releasing the limitation on the mounting post 212. At this time, pull out the mounting post 212 upward so that the mounting post 212 can be removed from the interior of the circular groove 211, thereby disassembling the mounting post 212, thereby enabling the disassembly of the propeller body 233, thus facilitating the disassembly and replacement of the propeller body 233. By setting the material of the propeller body 233 as carbon fiber, the propeller body 233 can have the characteristics of high rigidity, high tensile strength, low weight, high chemical resistance, high temperature resistance and low thermal expansion.

[0042] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A carbon fiber unmanned aerial vehicle (UAV) component, comprising a main body module (100) and four component assembly / disassembly modules (200), characterized in that: The main module (100) includes a drone body (110), and four mounting blocks (120) are fixedly connected to the surface of the drone body (110). The four parts assembly and disassembly modules (200) are respectively set on the four mounting blocks (120). The parts assembly / disassembly module (200) includes an assembly component (210) disposed on one of the mounting blocks (120), a stabilizing component (220) disposed between the assembly component (210) and one of the mounting blocks (120), and a propeller assembly (230) disposed on the assembly component (210).

2. A carbon fiber UAV component according to claim 1, characterized in that: The mounting assembly (210) includes a circular groove (211) formed on one of the mounting blocks (120), and a mounting post (212) is movably inserted into the interior of the circular groove (211).

3. A carbon fiber UAV component according to claim 2, characterized in that: The stabilizing component (220) includes two fixing plates (221) that are fixedly connected to both sides of one of the mounting blocks (120). Each of the two fixing plates (221) is rotatably connected to a collar (222) on the opposite side. A double-ended threaded pin (223) is movably inserted between the two collars (222), one of the mounting blocks (120), and the mounting post (212).

4. A carbon fiber UAV component according to claim 3, characterized in that: The stabilizing component (220) also includes two easy-tightening nuts (224) that are threaded to both ends of the double-ended threaded pin (223), and the two easy-tightening nuts (224) abut against the two collars (222) respectively.

5. A carbon fiber UAV component according to claim 4, characterized in that: The propeller assembly (230) includes a mounting groove (231) formed on the top of the mounting post (212), a drive motor (232) is fixedly connected inside the mounting groove (231), and the output end of the drive motor (232) extends to the top of the mounting post (212).

6. A carbon fiber drone component according to claim 5, characterized in that: The propeller assembly (230) also includes a propeller body (233) fixedly connected to the output end of the drive motor (232).

7. A carbon fiber UAV component according to claim 6, characterized in that: The propeller body (233) can be made of carbon fiber.

8. A carbon fiber UAV component according to claim 7, characterized in that: The main module (100) also includes multiple weight-reducing grooves (130) respectively opened inside multiple mounting blocks (120).

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