Outer end structure of rotor wing of composite unmanned aerial vehicle

Abstract

The utility model relates to the technical field of rotors on unmanned aerial vehicles, and particularly provides an outer end structure of a composite unmanned aerial vehicle rotor. The wing comprises a wing body, a bolt groove is formed in one end of the wing body, a first balance weight mechanism is in threaded connection with the interior of the bolt groove, the first balance weight mechanism comprises a threaded shell, a magnet ring is fixedly connected to one side of the threaded shell, an inner threaded rod is fixedly connected to the interior of the magnet ring, and a second threaded rod is fixedly connected to the interior of the inner threaded rod. By arranging the wings and the first balance weight mechanism, the balance weight of the rotor wing can be conveniently adjusted to meet different flight requirements, meanwhile, magnetic fluid is used as a balance weight material, the density is high, the magnetic fluid can be conveniently adsorbed and fixed through the magnet ring, and the magnetic fluid can be used as the balance weight material. The stability and the reliability of the structure are guaranteed, the number of the balancing weights is reduced, and the working efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of rotors on unmanned aerial vehicles, and in particular to an outer end structure of a composite unmanned aerial vehicle rotor. Background Art

[0002] Unmanned helicopters are currently being used in commercial fields on a large scale, such as aerial photography and UAV plant protection, from their traditional military applications. Although the research and development and large-scale production of UAVs in recent years have reduced their costs a lot, their prices are still relatively expensive in the commercial field that pursues economic benefits. This is also one of the obstacles to their large-scale popularization and application. Therefore, how to reduce the manufacturing and use costs of UAVs is still a theme. The high price of UAVs comes from their irreplaceable engine technology and related core components, such as rotors. At present, the rotors on single-rotor unmanned helicopters are basically made of carbon fiber composite rotors. At present, when making carbon fiber composite rotors, first clean the mold, then apply a release agent, and then connect the cut carbon fiber cloth to the set thickness layer by layer in the mold by bonding, and then put it into the inner interlayer. Since the rotor needs sufficient centrifugal force during flight, it is necessary to implant a counterweight in the rotor to generate this centrifugal force in the production of the rotor. In this process, a lead block is also placed inside the rotor to form a counterweight. After the rotor is made, the lead block is firmly embedded in the rotor.

[0003] After searching, the outer end structure of the aluminum-plastic composite UAV rotor with application number "202121812537.X" includes a rotor body made of an aluminum profile with a hollow cavity, the hollow cavity has a reinforcing rib, and the reinforcing rib divides the hollow cavity into multiple sub-cavities. A plastic blade tip is fixedly connected to the outer end of the rotor body. The shape of the plastic blade tip is made according to the shape of the outer end of the rotor. The reinforcing rib on the end face of the rotor body has a threaded hole along the length of the rotor. There are one or more threaded holes. Bolt holes corresponding to the screw holes are opened on the plastic blade tip. Bolts are inserted in the bolt holes. The bolts pass through the plastic blade tip and are screwed into the threaded holes. The plastic blade tip of this structure can be firmly combined with the rotor body as one.

[0004] The inventor of this application found that there are the following problems in the practical use process:

[0005] The outer end structure of the current composite UAV rotor relies on different types of counterweights, which leads to a variety of counterweight models. During installation, it is necessary to select the appropriate counterweight for installation. On the one hand, the selection is more complicated, and on the other hand, different types of counterweights need to be produced, which increases inventory management and production costs.

[0006] Therefore, it is necessary to provide an outer end structure of a composite UAV rotor to solve the above technical problems. Utility Model Content

[0007] The technical problem to be solved by the utility model is to solve the problem of a large number of counterweight block models. Aiming at the above-mentioned defects of the prior art, an outer end structure of a composite UAV rotor is provided.

[0008] To achieve the above-mentioned purpose, the technical solution of the utility model is: an outer end structure of a composite UAV rotor, including a wing, a bolt groove is opened inside one end of the wing, the internal thread of the bolt groove is connected to a first counterweight mechanism, the first counterweight mechanism includes a threaded shell, one side of the threaded shell is fixedly connected to a magnet ring, the inside of the magnet ring is fixedly connected to an internal threaded rod, one side of the threaded shell is fixedly connected to a sealing ring, the inner side of the sealing ring is fixedly connected to the internal threaded rod, a feeding hole is opened on the sealing ring, a rubber plug is clamped inside the feeding hole, and a magnetic fluid is adsorbed on one side of the magnet ring.

[0009] By adopting the above technical solution and setting bolt grooves, the counterweight mechanism can be easily installed and disassembled, which provides convenience for adjusting the balance of the rotor. The first counterweight mechanism uses magnetic fluid as the counterweight material. Through the adsorption effect of the magnet ring, the amount of magnetic fluid can be increased or decreased as needed, thereby accurately adjusting the counterweight of the rotor to achieve optimal flight stability.

[0010] It is further provided that one end of the wing is snap-connected with a wing tip via a snap-fit ​​mechanism, and the snap-fit ​​mechanism comprises an extension plate and an extension slot.

[0011] By adopting the above technical solution, a quick and firm connection can be achieved by locking one end of the wing to the wingtip through a locking mechanism. This is more convenient than traditional bolt connection or welding methods, can save assembly and disassembly time, and improve work efficiency.

[0012] It is further provided that a clamping slot is provided on the extension plate, and a clamping block is fixedly connected to the inner wall of the extension slot.

[0013] By adopting the above technical solution, a simple and effective mechanical connection method is provided by opening a slot on the extension plate and fixing a connecting block on the inner wall of the extension slot. The pairing of the slot and the block makes the connection between the wing and the wingtip more secure, reducing the risk of loosening or falling off due to vibration or other external forces during flight.

[0014] It is further provided that the clamping slot and the clamping block are matched with each other, a bolt hole is provided on one side of the wing tip, and a bolt is provided inside the bolt hole.

[0015] By adopting the above technical solution, the matching design of the card slot and the card block ensures a tight connection between the wing and the wingtip, enhances the stability and reliability of the structure, makes the assembly process easier, and at the same time provides a stable connection method that can effectively resist vibration and impact during flight.

[0016] It is further provided that the internal thread of the bolt groove is connected with a second counterweight mechanism, and the second counterweight mechanism comprises a double-sided threaded shell, and one side of the inner wall of the double-sided threaded shell is fixedly connected by a connecting block and an internal threaded rod.

[0017] By adopting the above technical solution, the second counterweight mechanism is threadedly connected inside the bolt groove as an alternative embodiment, which increases the flexibility and diversity of the UAV rotor counterweight, allowing users to choose a suitable counterweight mechanism according to different flight requirements or environmental conditions, thereby optimizing the flight performance of the UAV.

[0018] It is further provided that the inner thread of the double-sided threaded shell is connected with a pressure ring, and one side of the pressure ring is fixedly connected with a control rod.

[0019] By adopting the above technical solution, a pressure ring is connected to the internal threads of the double-sided threaded shell so that the weight of the counterweight mechanism can be adjusted. By rotating the pressure ring, its position inside the double-sided threaded shell can be changed, thereby adjusting the overall weight of the counterweight mechanism, providing a flexible counterweight adjustment method to meet the needs of different flight conditions.

[0020] It is further provided that the pressure ring and the internal threaded rod are slidably connected.

[0021] By adopting the above technical solution, the sliding connection design between the pressure ring and the internal threaded rod ensures that the pressure ring can move freely on the internal threaded rod, making the weight adjustment of the counterweight mechanism more flexible and convenient. The user can easily adjust the position of the pressure ring as needed to change the counterweight.

[0022] Compared with the related art, the outer end structure of a composite UAV rotor provided by the utility model has the following beneficial effects:

[0023] The utility model provides an outer end structure of a composite UAV rotor. By arranging a wing and a first counterweight mechanism, the counterweight of the rotor can be conveniently adjusted to meet different flight requirements. At the same time, magnetic fluid is used as a counterweight material, which not only has a higher density but can also be conveniently adsorbed and fixed by a magnet ring, making the counterweight process more flexible and precise. The wing, the counterweight mechanism and the wing tip can be firmly connected together through simple screw-in and threaded connection operations, thereby ensuring the stability and reliability of the structure, simplifying the number of counterweight blocks and improving work efficiency.

[0024] The utility model provides an outer end structure of a composite UAV rotor, which adopts a snap-fit ​​mechanism and a wing tip, and utilizes a snap-fitting mode of a snap slot and a snap block to realize a fast and reliable connection between the wing and the wing tip. The design of the snap slot and the snap block has a certain elasticity, which can adapt to the dimensional change of the wing during thermal expansion and contraction, thereby maintaining the stability and reliability of the connection, reducing the risk of loose connection or damage due to temperature change, and enhancing the durability and safety of the UAV rotor.

[0025] The utility model provides an outer end structure of a composite UAV rotor, which adopts a second counterweight mechanism, and realizes the filling and pressing of counterweight particles by arranging a pressure ring, thereby completing the adjustment of the counterweight. The design of using a control rod and a pressure ring makes the counterweight adjustment simpler and more convenient. The user can easily unscrew the pressure ring by holding the control rod, fill it with metal powder, and then screw it on again to press it tightly, thereby quickly completing the counterweight adjustment, effectively preventing the metal powder from shaking during the rotation of the wing, and ensuring the stability and reliability of the counterweight. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0027] Figure 2 It is a schematic diagram of the explosion three-dimensional structure of the utility model;

[0028] Figure 3 It is a schematic diagram of the half-section structure of the wing tip of the utility model;

[0029] Figure 4 It is a half-section structural schematic diagram of the first counterweight mechanism of the utility model;

[0030] Figure 5 It is a half-section structural schematic diagram of the second breeding mechanism of the utility model.

[0031] Numbers in the figure: 1. wing; 2. bolt groove; 3. first counterweight mechanism; 301. threaded shell; 302. magnet ring; 303. internal threaded rod; 304. sealing ring; 305. feeding hole; 306. rubber plug; 307. magnetic fluid; 4. snap-fit ​​mechanism; 401. extension plate; 402. extension groove; 403. snap groove; 404. snap block; 5. wing tip; 6. bolt hole; 7. second counterweight mechanism; 701. double-sided threaded shell; 702. connecting block; 703. pressure ring; 704. control rod; 8. bolt. DETAILED DESCRIPTION

[0032] In order to facilitate the understanding of the present invention, the present invention will be described more comprehensively with reference to the accompanying drawings. The accompanying drawings show typical embodiments of the present invention.

[0033] Embodiment 1:

[0034] like Figure 1-5 As shown, the outer end structure of a composite UAV rotor of the utility model includes a wing 1, a bolt groove 2 is provided inside one end of the wing 1, a first counterweight mechanism 3 is connected to the inner thread of the bolt groove 2, and the first counterweight mechanism 3 includes a threaded shell 301, a magnet ring 302 is fixedly connected to one side of the threaded shell 301, an internal threaded rod 303 is fixedly connected to the inside of the magnet ring 302, a sealing ring 304 is fixedly connected to one side of the threaded shell 301, the inner side of the sealing ring 304 is fixedly connected to the internal threaded rod 303, a feeding hole 305 is provided on the sealing ring 304, a rubber plug 306 is engaged with the inner side of the feeding hole 305, and a magnetic ring 302 is adsorbed on one side of the magnet ring 302. The magnetic fluid 307 can be easily installed and disassembled by setting the bolt groove 2, which provides convenience for adjusting the balance of the rotor. The first counterweight mechanism 3 uses the magnetic fluid 307 as the counterweight material. Through the adsorption effect of the magnet ring 302, the amount of magnetic fluid can be increased or decreased as needed, so as to accurately adjust the counterweight of the rotor to achieve optimal flight stability. At the same time, the sealing ring 304 and the rubber plug 306 in the technical solution ensure the sealing of the counterweight mechanism and prevent the leakage of the magnetic fluid 307, thereby ensuring the stability and durability of the counterweight, extending the service life of the counterweight mechanism, reducing the frequency of maintenance and replacement, and reducing the cost of use.

[0035] like Figure 2 and Figure 3 As shown, one end of the wing 1 is connected to the wing tip 5 through the locking mechanism 4, and the locking mechanism 4 includes an extension plate 401 and an extension slot 402. By locking one end of the wing 1 to the wing tip 5 through the locking mechanism 4, a quick and firm connection can be achieved. Compared with the traditional bolt connection or welding method, it is more convenient, can save assembly and disassembly time, and improve work efficiency. At the same time, the design of the locking mechanism 4, including the extension plate 401 and the extension slot 402, increases the stability and reliability of the connection. The extension plate 401 can be inserted into the extension slot 402 to form a tight fit to prevent the wing tip 5 from loosening or falling off during flight, thereby ensuring the flight safety of the UAV. Even if there is a docking error to a certain extent, the elastic deformation of the locking mechanism 4 can adapt to and ensure the stability of the connection.

[0036] like Figure 2 and Figure 3As shown, a slot 403 is provided on the extension plate 401, and a block 404 is fixedly connected to the inner wall of the extension slot 402. By providing the slot 403 on the extension plate 401 and fixing the block 404 on the inner wall of the extension slot 402, a simple and effective mechanical connection method is provided. The pairing of the slot 403 and the block 404 makes the connection between the wing 1 and the wingtip 5 more secure, reducing the risk of loosening or falling off due to vibration or other external forces during flight. At the same time, the precise matching of the slot 403 and the block 404 can ensure that the wing 1 and the wingtip 5 are in the correct relative position when connected, thereby ensuring the overall performance and flight stability of the rotor, and facilitating maintenance and replacement of components, thereby improving the maintainability and service life of the UAV.

[0037] like Figure 2 and Figure 3 As shown, the slot 403 and the block 404 are matched with each other, a bolt hole 6 is provided on one side of the wing tip 5, and a bolt 8 is arranged inside the bolt hole 6. The matching design of the slot 403 and the block 404 ensures a tight connection between the wing 1 and the wing tip 5, enhances the stability and reliability of the structure, makes the assembly process simpler, and provides a stable connection method, which can effectively resist vibration and impact during flight. At the same time, the bolt hole 6 provided on one side of the wing tip 5 is combined with the bolt 8 arranged inside, which further strengthens the connection between the wing 1 and the wing tip 5. The bolt connection has high strength and reliability, and can prevent connection failure caused by wear of the locking mechanism 4 or unexpected circumstances.

[0038] During implementation, first, when it is necessary to install a counterweight, first remove the rubber plug 306 on the sealing ring 304, pour a proper amount of magnetic fluid 307 into it, the magnetic fluid 307 is adsorbed by the magnet ring 302 to form a counterweight, then screw the first counterweight mechanism 3 into the bolt slot 2, and then connect the wing tip 5 with the block 404 on the wing tip 5 through the slot 403 on the extension plate 401, so that the wing can maintain a reliable connection with the wing tip 5 even when the wing expands and contracts due to heat, and finally connect the wing tip 5 to the wing 1 through the bolt 8 and the internal threaded rod 303 to complete the connection.

[0039] Embodiment 2:

[0040] like Figure 5As shown, on the basis of embodiment one, the utility model provides a technical solution: the internal thread of the bolt groove 2 is connected with a second counterweight mechanism 7, and the second counterweight mechanism 7 includes a double-sided threaded shell 701. One side of the inner wall of the double-sided threaded shell 701 is fixedly connected by a connecting block 702 and an internal threaded rod 303. The internal thread of the bolt groove 2 is connected to the second counterweight mechanism 7 as a replacement embodiment, which increases the flexibility and diversity of the UAV rotor counterweight, so that the user can choose a suitable counterweight mechanism according to different flight requirements or environmental conditions, thereby optimizing the flight performance of the UAV. At the same time, the double-sided threaded shell 701 of the second counterweight mechanism 7 provides a reliable guiding restriction for the pressure ring 703, so that the pressure ring 703 can effectively prevent the internal counterweight particles from shaking during flight, thereby improving the safety of the UAV flight.

[0041] like Figure 5 As shown, the internal threads of the double-sided threaded shell 701 are connected with a pressure ring 703, and one side of the pressure ring 703 is fixedly connected with a control rod 704. The internal threads of the double-sided threaded shell 701 are connected with the pressure ring 703, so that the weight of the counterweight mechanism can be adjusted. By rotating the pressure ring 703, its position in the double-sided threaded shell 701 can be changed, thereby adjusting the overall weight of the counterweight mechanism, providing a flexible counterweight adjustment method to meet the needs of different flight conditions. At the same time, the control rod 704 fixedly connected to one side of the pressure ring 703 provides a convenient operation interface for the user. By rotating the control rod 704, the user can easily adjust the position of the pressure ring 703 and then change the counterweight.

[0042] like Figure 5 As shown, the pressure ring 703 and the internal threaded rod 303 are slidingly connected. The sliding connection design of the pressure ring 703 and the internal threaded rod 303 ensures that the pressure ring 703 can move freely on the internal threaded rod 303, making the weight adjustment of the counterweight mechanism more flexible and convenient. The user can easily adjust the position of the pressure ring 703 as needed to change the counterweight. At the same time, since the connection between the pressure ring 703 and the internal threaded rod 303 is sliding, when adjusting the counterweight, the pressure ring 703 can move smoothly on the internal threaded rod 303, avoiding jamming or sudden jumping, thereby ensuring the accuracy and reliability of the counterweight adjustment.

[0043] During implementation, first, as a replacement for the first counterweight mechanism, hold the control rod 704, unscrew the pressure ring 703, and then fill in the metal powder for counterweight, and then re-select the pressure ring 703 into the double-sided threaded shell 701, and then rotate the control rod 704 so that the pressure ring 703 can press the metal powder to prevent it from shaking during the rotation of the wing, and then screw the second counterweight mechanism 7 into the bolt groove 2, and then connect the wing tip 5 with the card slot 403 on the extension plate 401 and the card block 404 on the wing tip 5, and finally connect the wing tip 5 and the wing 1 through the bolt 8 to complete the connection.

[0044] The advantages of this technical solution in practical applications include but are not limited to the following:

[0045] 1. Adjustable counterweight to achieve precise weight balance;

[0046] 2. The block connection method prevents thermal expansion and contraction.

[0047] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An outer end structure of a composite UAV rotor, characterized in that: The invention comprises a wing (1), wherein a bolt groove (2) is provided inside one end of the wing (1), a first counterweight mechanism (3) is connected to the inner thread of the bolt groove (2), the first counterweight mechanism (3) comprises a threaded shell (301), a magnet ring (302) is fixedly connected to one side of the threaded shell (301), an internal threaded rod (303) is fixedly connected to the inner side of the magnet ring (302), a sealing ring (304) is fixedly connected to one side of the threaded shell (301), the inner side of the sealing ring (304) is fixedly connected to the internal threaded rod (303), a feeding hole (305) is provided on the sealing ring (304), a rubber plug (306) is engaged inside the feeding hole (305), and a magnetic fluid (307) is adsorbed on one side of the magnet ring (302).

2. The outer end structure of a composite UAV rotor according to claim 1, characterized in that: One end of the wing (1) is snap-connected to a wing tip (5) via a snap-connection mechanism (4), wherein the snap-connection mechanism (4) comprises an extension plate (401) and an extension slot (402).

3. The outer end structure of a composite UAV rotor according to claim 2, characterized in that: The extension plate (401) is provided with a clamping groove (403), and the inner wall of the extension groove (402) is fixedly connected with a clamping block (404).

4. The outer end structure of a composite UAV rotor according to claim 3, characterized in that: The clamping groove (403) and the clamping block (404) are matched with each other, a bolt hole (6) is provided on one side of the wing tip (5), and a bolt (8) is arranged inside the bolt hole (6).

5. The outer end structure of a composite UAV rotor according to claim 1, characterized in that: The internal thread of the bolt slot (2) is connected to a second counterweight mechanism (7), and the second counterweight mechanism (7) comprises a double-sided threaded shell (701), and one side of the inner wall of the double-sided threaded shell (701) is fixedly connected via a connecting block (702) and an internal threaded rod (303).

6. The outer end structure of a composite UAV rotor according to claim 5, characterized in that: The inner thread of the double-sided threaded shell (701) is connected to a pressure ring (703), and one side of the pressure ring (703) is fixedly connected to a control rod (704).

7. The outer end structure of a composite UAV rotor according to claim 6, characterized in that: The pressure ring (703) and the internal threaded rod (303) are slidably connected.

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