Carbon tube clamping device for heavy load multi-rotor unmanned aerial vehicle coaxial power set

Abstract

The application discloses a carbon pipe clamping device of a heavy-load multi-rotor unmanned aerial vehicle coaxial power set, which comprises a pipe clamping seat and a carbon pipe assembly, the pipe clamping seat is used for mounting a motor set and a speed regulating assembly; the carbon pipe assembly is mounted on the pipe clamping seat, and the carbon pipe assembly comprises a carbon pipe, an outer hoop fixing piece and an inner lining fixing piece, the inner lining fixing piece is mounted on the carbon pipe, and the outer hoop fixing piece is wrapped on the carbon pipe. Through the arrangement of the carbon pipe, the outer hoop fixing piece and the inner lining fixing piece fixed on the carbon pipe, the friction area and locking capacity of the carbon pipe are effectively improved through the mode of externally compressing the outer hoop and internally tensioning the inner lining, flight accidents caused by the carbon pipe in the flight process of the unmanned aerial vehicle are avoided, large load and high structural strength are realized, the shortcomings of the heavy-load multi-rotor coaxial power set are effectively solved, and the problems of structural strength and large load of the heavy-load multi-rotor unmanned aerial vehicle are solved to a great extent.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a carbon tube clamping device for a coaxial power system of a heavy-duty multi-rotor UAV. Background Technology

[0002] Heavy-duty multi-rotor drones represent a significant trend in the development of industrial drones, boasting excellent payload capacity and stable flight characteristics, making them suitable for various scenarios, including logistics transportation, emergency rescue, and military reconnaissance. However, most heavy-duty multi-rotor drones currently on the market use single-axis motors for power output, or their existing coaxial power kits have relatively light load capacities, failing to meet the requirements for large payload capacity. Summary of the Invention

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a carbon tube clamping device for a coaxial power kit for heavy-duty multi-rotor drones. This device achieves high load capacity and high structural strength, effectively solves the shortcomings of heavy-duty multi-rotor coaxial power kits, and largely solves the problems of structural strength and heavy load loading for heavy-duty multi-rotor drones.

[0004] The objective of this invention is achieved through the following technical solution:

[0005] A carbon nanotube clamping device for a coaxial power system of a heavy-duty multi-rotor UAV includes: a tube clamp seat and a carbon nanotube assembly.

[0006] The pipe clamp is used to install the motor unit and speed control components;

[0007] The carbon nanotube assembly is mounted on the tube clamp seat. The carbon nanotube assembly includes a carbon nanotube, an outer clamp fastener, and an inner liner fastener. The inner liner fastener is mounted on the carbon nanotube, and the outer clamp fastener is wrapped around the carbon nanotube.

[0008] In one embodiment, the carbon nanotube assembly further includes a first fastener for securing the outer hoop fastener and the inner liner fastener to the carbon nanotube, respectively.

[0009] In one embodiment, the carbon nanotube clamping device further includes a gasket mounted on the tube clamp seat, the gasket being used to fill the gap between the carbon nanotube assembly and the tube clamp seat.

[0010] In one embodiment, the carbon tube clamping device further includes a second fastener for mounting the gasket onto the tube clamp seat.

[0011] In one embodiment, the carbon tube clamping device further includes a protective rubber pad, which is mounted on the tube clamp seat.

[0012] In one embodiment, the carbon tube clamping device further includes a third fastener for mounting the protective pad onto the tube clamp seat.

[0013] In one embodiment, two outer hoop fasteners are provided, and the two outer hoop fasteners are respectively fitted onto the carbon tube;

[0014] In one of the outer hoop fasteners, the outer hoop fastener is provided with an upper and lower limit portion and an outer hoop left and right limit portion, the pipe clamp seat is provided with a pipe clamp upper and lower limit structure that cooperates with the upper and lower limit portion of the outer hoop, and the pipe clamp seat is provided with a pipe clamp left and right limit structure that cooperates with the left and right limit portion of the outer hoop.

[0015] In one embodiment, the upper and lower limiting parts of the outer hoop and the left and right limiting parts of the outer hoop are both elastically deformable structures.

[0016] In one embodiment, the motor assembly includes two motors, which are symmetrically arranged on the pipe clamp seat. The pipe clamp seat is provided with two motor mounting slots, and the two motors are respectively arranged in the two motor mounting slots.

[0017] The speed control assembly includes two speed controllers, which are symmetrically arranged on the pipe clamp seat. The pipe clamp seat has two speed control fixing slots, and the two speed controllers are respectively arranged in the two speed control fixing slots.

[0018] In one embodiment, the carbon tube clamping device further includes a front sealing cover and a rear sealing cover, which are respectively installed on the tube clamp seat.

[0019] The advantages and beneficial effects of this invention compared to the prior art are as follows:

[0020] This invention relates to a carbon fiber tube clamping device for a coaxial power system of a heavy-duty multi-rotor UAV. By incorporating a carbon fiber tube and external clamping and internal liner fixing components, the device effectively increases the friction area and locking capacity of the carbon fiber tube through external compression of the external clamping and internal tensioning of the internal liner. This prevents flight accidents caused by the carbon fiber tube spinning during UAV flight, achieving high load capacity and high structural strength. It effectively addresses the shortcomings of heavy-duty multi-rotor coaxial power systems and largely solves the problems of structural strength and heavy load loading in heavy-duty multi-rotor UAVs. The structure of this invention is safe and reliable, ensuring the safety and stability of the UAV during flight. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the carbon tube clamping device of the coaxial power kit for a heavy-duty multi-rotor UAV according to one embodiment of the present invention.

[0022] Figure 2 for Figure 1 The diagram shows a structural schematic of the carbon tube clamping device of the coaxial power system of a heavy-duty multi-rotor UAV from another perspective.

[0023] Figure 3 for Figure 1 The diagram shows a structural schematic of the carbon tube clamping device of the coaxial power system of a heavy-duty multi-rotor UAV from another perspective.

[0024] Figure 4 for Figure 1 The diagram shows an exploded view of the carbon tube clamping device of the coaxial power system of a heavy-duty multi-rotor UAV.

[0025] Figure 5 for Figure 1 A schematic diagram of the carbon tube assembly of the carbon tube clamping device shown.

[0026] Figure 6 for Figure 1 A schematic diagram of the carbon nanotube assembly of a carbon nanotube clamping device from another perspective;

[0027] Figure 7 for Figure 1 A schematic diagram of the carbon tube clamping device of another embodiment is shown;

[0028] Figure 8 for Figure 1 The diagram shows the structure of the protective rubber pad of the carbon tube clamping device. Detailed Implementation

[0029] To facilitate understanding of the present invention, a more complete description will be given below with reference to the accompanying drawings. Preferred embodiments of the invention are shown in the drawings. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a thorough and complete understanding of the disclosure of the invention.

[0030] Please see Figures 1-4 A carbon tube clamping device 30 for a coaxial power kit for a heavy-duty multi-rotor UAV is disclosed. The carbon tube clamping device of the present invention not only significantly improves the load capacity and structural strength, but also effectively overcomes the problems of poor load-bearing capacity and structural stability of traditional heavy-duty multi-rotor coaxial power kits, providing a powerful and effective solution for performance optimization and structural reinforcement of heavy-duty multi-rotor UAVs.

[0031] Furthermore, the carbon tube clamping device 30 includes a tube clamp seat 33 and a carbon tube assembly 31. The tube clamp seat 33 is used to install the motor unit 10 and the speed control assembly 20. As the supporting structure of the entire device, the tube clamp seat 33 not only provides a stable mounting platform for the motor unit and speed control assembly, ensuring accurate and efficient power transmission, but also, through its structural design, provides a solid and reliable supporting foundation for the carbon tube assembly, ensuring stability and durability under high load and heavy load operation. The carbon tube assembly is mainly composed of three parts: carbon tubes, outer clamp fasteners, and inner liner fasteners, which together constitute a key load-bearing unit in the UAV structure.

[0032] It should be noted that the carbon tube assembly 31 is mounted on the tube clamp seat 33. The carbon tube assembly 31 includes a carbon tube 311, an outer clamp fastener 313, and an inner liner fastener 314. The inner liner fastener is mounted on the carbon tube, and the outer clamp fastener is wrapped around the carbon tube. The carbon tube 311, with its lightweight, high strength, and corrosion resistance, serves as the main structural support material, effectively reducing the overall weight of the UAV while ensuring sufficient structural strength and rigidity. The inner liner fastener 314 fits tightly against the outer wall of the carbon tube, effectively enhancing the carbon tube's torsional resistance and axial stability, and effectively preventing deformation or damage caused by long-term heavy-duty use. The outer clamp fastener 313 is mounted on the outside of the carbon tube, forming a double reinforcement with the inner liner fastener through a locking mechanism, further improving the radial strength and overall stability of the carbon tube. The design of the outer clamp fastener also considers the need for easy installation and disassembly, ensuring convenient maintenance and replacement.

[0033] The interactions and connections between the various structures are close and efficient. The tube clamp provides a stable support frame for the carbon nanotube assembly, while the carbon nanotube assembly, through the synergistic action of the inner liner fastener and the outer hoop fastener, achieves comprehensive and multi-layered reinforcement of the carbon nanotubes, thereby ensuring the excellent performance and long-term reliability of the entire device under high-intensity and high-load working environments. This not only improves the load-bearing capacity of the UAV but also makes the structure of heavy-duty multi-rotor UAVs simpler and more reliable.

[0034] In this embodiment, please refer to Figure 5 and Figure 6 Two outer clamping fasteners 313 are provided, and each of the two outer clamping fasteners 313 is respectively fitted onto the carbon tube 311. Further, the inner sidewalls of the two outer clamping fasteners together form a large clamping outer circle. Two inner lining fasteners 314 are provided, and each of the two inner lining fasteners 314 is respectively installed on the carbon tube 311. The outer sidewalls of the two inner lining fasteners together form a large clamping outer circle and a large clamping outer circle. The large clamping outer circle and the large clamping outer circle together form a carbon tube clamping area, within which the carbon tube is clamped and fixed.

[0035] Furthermore, in one of the aforementioned outer hoop fasteners, the outer hoop fastener includes a first outer hoop fastener frame 313a and a second outer hoop fastener frame 313b, the first outer hoop fastener frame and the second outer hoop fastener frame being an integrally formed structure; the first outer hoop fastener frame has a first clearance cavity 313a-1 and two first outer hoop fastening holes, the two first outer hoop fastening holes communicating with the first clearance cavity; the second outer hoop fastener frame has a second clearance cavity 313b-1 and two second outer hoop fastening holes, the two second outer hoop fastening holes communicating with the second clearance cavity; wherein, the first clearance cavity and the second clearance cavity are used to achieve clearance and facilitate user installation and disassembly.

[0036] It should be noted that the first outer hoop fixing bracket 313a and the second outer hoop fixing bracket 313b are manufactured using an integrated molding technology, which not only ensures the structural robustness and durability but also greatly improves manufacturing precision and efficiency. The first outer hoop fixing bracket 313a has a first recessed cavity 313a-1 and two precisely positioned first outer hoop fixing holes. These two fixing holes are designed to connect with the recessed cavity, forming a spatial layout that facilitates installation and maintenance. Similarly, the second outer hoop fixing bracket 313b is also equipped with a second recessed cavity 313b-1 and two corresponding second outer hoop fixing holes. This design not only optimizes the installation process but also significantly enhances the structural flexibility and user-friendliness.

[0037] In another of the aforementioned outer clamp fasteners, there are a third outer clamp fastener 313c and a fourth outer clamp fastener 313d, which are integrally formed. The third outer clamp fastener has a third recessed cavity 313c-1 and two third outer clamp fastening holes, which communicate with the third recessed cavity. The fourth outer clamp fastener has a fourth recessed cavity 313d-1 and two fourth outer clamp fastening holes, which communicate with the fourth recessed cavity. The third and fourth recessed cavities are used to achieve recessed positioning, facilitating installation and disassembly by the user.

[0038] It should be noted that the other outer hoop fastener consists of a third outer hoop fastener 313c and a fourth outer hoop fastener 313d, which are tightly connected by advanced one-piece molding technology. This not only ensures the integrity and strength of the structure but also significantly improves manufacturing efficiency and precision. This design not only maximizes the utilization of material properties but also enhances structural strength. A third recessed cavity 313c-1 is provided on the third outer hoop fastener 313c, which optimizes the installation space and provides users with a more convenient assembly path. Simultaneously, two precisely positioned third outer hoop fastening holes connect to the third recessed cavity, forming a stable yet flexible assembly area. Similarly, the fourth outer hoop fastener 313d is also equipped with a corresponding fourth recessed cavity 313d-1 and two fourth outer hoop fastening holes. This layout not only enhances structural flexibility but also significantly improves the convenience of installation and maintenance.

[0039] In this embodiment, the carbon nanotube has a first connecting hole, a second connecting hole, a third connecting hole, and a fourth connecting hole. These four connecting holes are arranged in a ring around the carbon nanotube, and there are two of each type. It should be noted that the four sets of connecting holes—the first, second, third, and fourth connecting holes—are evenly arranged around the carbon nanotube, with each set containing two holes. This layout not only optimizes the stress distribution of the structure but also provides precise positioning points for subsequent fixing connections.

[0040] Furthermore, in one of the lining fasteners 314, the lining fastener includes a first lining fastener 314a and a second lining fastener 314b. The first and second lining fasteners are integrally formed. The first lining fastener has two first lining fastening holes, and the second lining fastener has two second lining fastening holes. It should be noted that one of the lining fasteners 314 is composed of the first lining fastener 314a and the second lining fastener 314b, and these two parts are connected to each other using an integral molding technology, forming a robust yet flexible whole. The first lining fastener 314a has two first lining fastening holes, while the second lining fastener 314b has two second lining fastening holes. These fastening holes not only provide precise mating points for subsequent fastening operations but also significantly enhance the stability and durability of the structure.

[0041] In another lining fastener, there are a third lining fastener 314c and a fourth lining fastener 314d. The third and fourth lining fasteners are integrally formed. The third lining fastener has two third lining fastening holes, and the fourth lining fastener has two fourth lining fastening holes. Thus, the other lining fastener is composed of the third lining fastener 314c and the fourth lining fastener 314d. These two parts also adopt an integrally formed structure, ensuring the integrity of the structure and improving its hardness and strength. The third lining fastener 314c has two third lining fastening holes, and the fourth lining fastener 314d also has two fourth lining fastening holes, which enhances the flexibility and adaptability of the structure.

[0042] It should be noted that the first clearance cavity and the first outer hoop fixing hole of the first outer hoop fixing frame, the first connecting hole on the carbon tube, and the first inner lining fixing hole of the first inner lining fixing piece are interconnected to form a first fixing channel 312a. After the first fastener 312 passes through the first fixing channel, it connects and fixes the first outer hoop fixing frame, the carbon tube, and the first inner lining fixing piece. The second clearance cavity and the second outer hoop fixing hole of the second outer hoop fixing frame, the second connecting hole on the carbon tube, and the fourth inner lining fixing hole of the fourth inner lining fixing piece are interconnected to form a second fixing channel 312b. After the first fastener 312 is placed in the second fixing channel, it connects the second outer hoop fixing frame, the carbon tube, and the fourth inner lining fixing piece. The third outer hoop fixing frame, the third outer hoop fixing hole, the third connecting hole on the carbon tube, and the third inner lining fixing hole of the third inner lining fixing piece are interconnected to form a third fixing cavity 312c. After the first fastener 312 is installed in the third fixing cavity, the third outer hoop fixing frame, the carbon tube, and the third inner lining fixing piece are connected and fixed. The fourth outer hoop fixing frame, the fourth outer hoop fixing hole, the fourth connecting hole on the carbon tube, and the second inner lining fixing hole of the second inner lining fixing piece are interconnected to form a fourth fixing cavity 312d. After the first fastener 312 is installed in the fourth fixing cavity, the fourth outer hoop fixing frame, the carbon tube, and the second inner lining fixing piece are connected and fixed.

[0043] Specifically, the first recessed cavity on the first outer hoop fixing frame is interconnected with the first outer hoop fixing hole, the first connecting hole on the carbon tube, and the first inner lining fixing hole on the first inner lining fixing plate, together forming a precise first fixing channel 312a. When the first fastener 312 passes through this channel, it firmly connects the first outer hoop fixing frame, the carbon tube, and the first inner lining fixing plate together, forming a tight, stable, and reliable fixing system.

[0044] In this way, the fixing holes on the first inner lining fixing piece and the second inner lining fixing piece can be connected and passed through the first fixing cavity and the fourth fixing cavity for fixing. Since the first inner lining fixing piece and the second inner lining fixing piece are an integral structure, the friction area and locking ability of the carbon tube 311 can be effectively improved by externally pressing the outer hoop fixing member and internally tightening the inner lining fixing member, thereby avoiding flight accidents caused by the carbon tube 311 spinning during the flight of the UAV.

[0045] Within the internal structure of the UAV frame, the first and second inner lining fixing plates are integrally molded to ensure structural integrity and stability. These two inner lining fixing plates each have fixing holes that match specific connecting holes on the carbon nanotubes, providing precise docking points for subsequent fixing operations. In the overall layout of the UAV carbon nanotube fixing frame, these outer hoop fixing frames are interconnected through their fixing holes, specific connecting holes on the carbon nanotubes, and fixing holes on the inner lining fixing components, forming a complex and precise fixing structure. Specifically, the third outer hoop fixing frame and its related components (including the corresponding connecting holes on the carbon nanotubes and the fixing holes on the inner lining fixing components) form an independent fixing cavity, while the fourth outer hoop fixing frame and its matching components form another complementary fixing cavity. By inserting first fasteners (such as bolts and screws) through these fixing cavities, a strong and stable connection is established between the outer hoop fixing components, the carbon nanotubes, and the inner lining fixing components. This design not only achieves a tight connection between the structures, but also significantly increases the friction area and locking capability between the carbon tube and the fixing components through the synergistic effect of the outer clamping fastener and the inner liner fastener. This dual locking mechanism not only enhances the overall stability of the structure, but also effectively prevents structural loosening or deformation that may occur during high-speed flight of the UAV, thereby ensuring flight safety and reliability.

[0046] In the UAV system, a connection is established between the inner liner fixing component, the outer hoop fixing component, and the carbon nanotube. Specifically, the fixing holes on the first and second inner liner fixing plates correspond to the first and second connecting holes on the carbon nanotube, respectively. By inserting fasteners through these holes, a secure connection is established between the inner liner fixing component and the carbon nanotube. Similarly, the third and fourth inner liner fixing plates mate with the third and fourth connecting holes on the carbon nanotube, forming another independent fixing system.

[0047] Furthermore, the carbon nanotube assembly also includes a first fastener 312, which is used to fix the outer clamp fixing member and the inner liner fixing member to the carbon nanotube respectively. The first fastener 312, as a locking component for connection and fixation, ensures a tight fit and reliable fixation between the various components of the carbon nanotube assembly. This not only improves the overall stability of the structure but also significantly enhances the reliability of the heavy-duty multi-rotor UAV in extreme conditions.

[0048] Specifically, the first fastener 312 acts as a reinforcement in the carbon nanotube assembly. The first fastener 312 is positioned between the outer clamp and the carbon nanotube. Through tightening, the screw of the first fastener generates strong radial pressure, tightly and evenly pressing the outer clamp onto the outer surface of the carbon nanotube. This not only enhances the radial support of the carbon nanotube but also effectively prevents loosening due to vibration or external forces, ensuring the structural integrity of the carbon nanotube assembly under long-term, high-load operation. The outer clamp and the inner liner complement each other; the first fastener 312 simultaneously and firmly pulls the inner liner onto the carbon nanotube. By setting the first fastener 312, the inner liner is tightly fitted to the carbon nanotube, forming an additional protective layer that effectively improves the torsional strength and axial stability of the carbon nanotube. Furthermore, the inner liner, based on the thermal expansion and contraction characteristics of the carbon nanotube, ensures that the carbon nanotube assembly maintains good structural performance under different ambient temperatures. The first fastener 312 not only achieves a firm connection between the various components of the carbon nanotube assembly through physical fastening, but also optimizes the stress state of the carbon nanotubes by distributing pressure and tension evenly, thereby significantly improving the load-bearing capacity and structural strength of the entire carbon nanotube assembly.

[0049] Thus, by setting up carbon tubing and fixing external and internal fasteners to it—that is, by externally pressing the external fastener and internally tightening the internal fastener—the friction area and locking ability of the carbon tubing can be effectively increased. This avoids flight accidents caused by the carbon tubing spinning during UAV flight, achieving high load capacity and high structural strength. It effectively solves the shortcomings of heavy-load multi-rotor coaxial power systems, and largely addresses the structural strength and heavy load-bearing issues of heavy-load multi-rotor UAVs. The structure of this invention is safe and reliable, ensuring the safety and stability of the UAV during flight.

[0050] Please see Figure 4The carbon nanotube clamping device further includes a gasket 32, which is mounted on the tube clamp seat and fills the gap between the carbon nanotube assembly and the tube clamp seat. Further, the carbon nanotube clamping device includes a second fastener 34, which is used to mount the gasket onto the tube clamp seat. Thus, the gasket 32 ​​fills the gap resulting from the assembly of the carbon nanotube assembly 31 and the tube clamp seat 33, and the second fastener 34 secures the gasket 32 ​​within the tube clamp seat 33. The gasket 32 ​​is optional and is used to fill gaps caused by the machining precision of the components; the number is not limited to two, and optionally, multiple or even zero gaskets 32 may be used.

[0051] It should be noted that by setting the gasket 32 ​​and the second fastener 34, the stability and durability of the device can be improved together, ensuring a seamless connection between the carbon nanotube assembly and the tube clamp. The gasket 32 ​​is installed between the tube clamp and the carbon nanotube assembly, its main function being to fill the tiny gaps between them, thereby eliminating potential assembly errors and tolerance accumulation, achieving a tighter and more stable connection. The use of the gasket 32 ​​not only improves the overall rigidity of the structure but also effectively prevents components from loosening or being damaged due to vibration or long-term stress concentration. Its material is selected as a high-strength, wear-resistant, and somewhat elastic material to ensure that the gasket can continuously provide stable support and cushioning in complex and variable flight environments. The second fastener 34, as the key link connecting the gasket 32 ​​and the tube clamp, can be in the form of a high-strength screw or bolt. Tightening it securely fixes the gasket to the tube clamp, thereby ensuring a tight fit and stable connection between the carbon nanotube assembly and the tube clamp. The installation of the second fastener ensures that it can withstand loads and stresses under extreme conditions while maintaining the integrity and durability of the structure. The interaction and connection between the gasket 32 ​​and the second fastener 34 work together between the carbon nanotube assembly and the tube clamp, achieving seamless connection and efficient coordination between the two by filling the gap and applying a tightening force. This not only improves the overall stability and durability of the carbon nanotube clamping device, but also provides more reliable structural support for heavy-duty multi-rotor UAVs when facing complex flight conditions.

[0052] The protective rubber pad 35 is made of soft and elastic material, allowing it to fit snugly against the front end of the tube clamp 33. The main function of the protective rubber pad 35 is to provide an additional protective layer for the wiring harness of the motor assembly 10 and speed control component 20 that runs inside the carbon tube assembly 31. It effectively absorbs vibration and buffers impacts, preventing wear of the wiring harness due to long-term friction or external forces, thus ensuring the integrity of the wiring harness and the stability of signal transmission. The third fastener 36, serving as a fixing component connecting the protective rubber pad 35 and the tube clamp 33, is in the form of a high-strength screw or bolt. Tightening it securely fixes the protective rubber pad 35 to the front end of the tube clamp 33. This not only ensures a tight fit between the protective rubber pad 35 and the tube clamp 33 but also prevents displacement of the protective rubber pad under vibration or external forces by applying appropriate tightening force, thereby ensuring the long-term stability and reliability of the wiring harness protection system. Thus, the interaction and connection between the protective rubber pad 35 and the third fastener 36 constitute the external wiring harness protection system. These components work together on the carbon tube clamping device, providing an additional protective layer and applying a tightening force to effectively prevent wear of the wiring harnesses of the motor assembly 10 and speed control component 20 inside the carbon tube assembly 31. This not only improves the overall stability and durability of the UAV's power system but also provides a more robust guarantee for the safe flight of the UAV.

[0053] In this embodiment, one of the outer hoop fixing members 313 is provided with an upper and lower limiting part 3131 and an outer hoop left and right limiting part 3132. The pipe clamp seat 33 is provided with a pipe clamp upper and lower limiting structure 331 that cooperates with the upper and lower limiting part of the outer hoop, and the pipe clamp seat is provided with a pipe clamp left and right limiting structure 332 that cooperates with the left and right limiting part of the outer hoop. In this embodiment, both the upper and lower limiting part and the left and right limiting part of the outer hoop are elastically deformable structures. Thus, the upper and lower limiting part 3131 and the left and right limiting part 3132 of the outer hoop are processed into elastically deformable shapes. By limiting the assembly of the pipe clamp seat 33 with the carbon tube assembly 31, deformation and resonance caused by the swaying of the UAV during flight can be effectively avoided.

[0054] In the carbon tube clamping device structure of the coaxial power kit for heavy-duty multi-rotor UAVs, the upper and lower limiting parts 3131 and the left and right limiting parts 3132 on the outer hoop fixing component, along with the upper and lower limiting structures 331 and the left and right limiting structures 332 on the corresponding tube clamp seat 33, not only greatly improve the stability of the device but also effectively suppress swaying, deformation, and resonance phenomena during UAV flight. Both the upper and lower limiting parts 3131 and the left and right limiting parts 3132 adopt elastically deformable structures, meaning they can deform and adjust their shape to a certain extent according to the actual needs during installation, adapting to the fit and sway between the carbon tube assembly 31 and the tube clamp seat 33. This structure not only enhances the flexibility of the assembly process but also ensures a tight and stable connection between the limiting parts and the limiting structures, effectively preventing component loosening due to vibration or external forces. The upper and lower limiting structures 331 and the left and right limiting structures 332 of the pipe clamp, through the setting of these two structures, ensure proper cooperation with the upper and lower limiting parts 3131 and the left and right limiting parts 3132 of the outer hoop. This not only provides the necessary limiting function but also, through its own structure, provides additional support and protection for the carbon tube assembly 31. When the outer hoop fixing member and the pipe clamp seat 33 are tightly connected through the cooperation of the limiting parts and limiting structures, the entire carbon tube clamping device forms a stable and reliable frame, providing a solid foundation for the safe operation of the UAV power system.

[0055] Further, please refer to Figure 7The upper and lower limiting structure 331 of the pipe clamp includes a top pressing member 3311 and a bottom supporting member 3312. The top pressing member and the bottom supporting member are used to work together on the outer hoop fixing member, that is, the top pressing member and the bottom supporting member are used to clamp the two outer hoop fixing members. Specifically, the top pressing member is used to press against the top of the upper and lower limiting part of the outer hoop of the two outer hoop fixing members, and the bottom supporting member is used to support the bottom of the upper and lower limiting part of the outer hoop of the two outer hoop fixing members. Meanwhile, the left and right limiting structure 332 of the tube clamp includes a left clamping member 3321 and a right clamping member 3322. The left clamping member and the right clamping member work together on the outer hoop fixing member, that is, the left clamping member and the right clamping member clamp the two outer hoop fixing members. Specifically, the left clamping member is used to press against the outer wall of one of the outer hoop fixing members, and the right clamping member is used to press against the outer wall of the other outer hoop fixing member at a relative position. In this way, through the top pressing member 3311, the bottom supporting member 3312, the left clamping member 3321, and the right clamping member 3322, the two outer hoop fixing members can be clamped and fixed more securely, which can further fix the position of the carbon tube and effectively avoid deformation and resonance caused by the swaying of the UAV during flight. In addition, by setting the top pressing member 3311, the bottom supporting member 3312, the left clamping member 3321 and the right clamping member 3322 to a shape that can be elastically deformed, the resonance of the drone during flight is filtered out more effectively.

[0056] It should also be noted that the limiting structure system of the tube clamp integrates a dual stabilizing mechanism for both vertical and horizontal movement. Specifically, it consists of a vertical limiting structure 331 composed of a top pressing member 3311 and a bottom supporting member 3312, and a horizontal limiting structure 332 composed of a left clamping member 3321 and a right clamping member 3322. These two structures work together to precisely and firmly fix the outer clamping member, thereby ensuring the stable and reliable position of the carbon tube.

[0057] In the upper and lower limiting structure 331, the top pressing member 3311 can accurately press against the top of the upper and lower limiting parts of the two outer hoop fixing members, effectively preventing upward movement caused by external forces or vibrations. Meanwhile, the bottom supporting member 3312 firmly supports the bottom of the upper and lower limiting parts of the two outer hoop fixing members, forming a stable support that effectively resists downward pressure and possible deformation. The two complement each other, ensuring vertical stability and significantly improving the overall structural rigidity through their close cooperation.

[0058] Meanwhile, left and right limiting structures 332 are positioned on the left and right sides, further enhancing the overall stability. The left clamping member 3321 is tightly fitted against the outer wall of one of the outer hoop fixing members, effectively preventing lateral displacement of that side wall through its tight wrapping and pressure. The right clamping member 3322 presses against the opposite position of the outer wall of the other outer hoop fixing member, ensuring a tight fit between the two in the horizontal direction, thus forming another solid limiting structure in the horizontal direction. The close cooperation between these two not only ensures stability in the left and right directions but also effectively suppresses any possible twisting or deformation through their uniform clamping force.

[0059] It is particularly worth mentioning that the top pressing component 3311, the bottom supporting component 3312, the left clamping component 3321, and the right clamping component 3322 are all made of materials with excellent elastic deformation capabilities. This not only makes the structure adaptable and able to flexibly cope with various vibrations and impacts during the flight of the UAV, but also effectively filters out resonance caused by flight, thereby greatly reducing fatigue damage to the UAV structure and improving the stability and safety of flight.

[0060] In summary, through the limiting structure system of the top pressing component 3311, the bottom supporting component 3312, the left clamping component 3321, and the right clamping component 3322, the two outer clamping fasteners are firmly and stably clamped and fixed, and the position of the carbon tube is precisely controlled. This not only enhances the structural strength and stability of the UAV, but also effectively avoids deformation and resonance problems caused by factors such as swaying and vibration during flight, thereby improving the safety and efficiency of the UAV.

[0061] Please see Figure 4 The carbon nanotube clamping device further includes a wire-protecting rubber pad 35, which is mounted on the tube clamp seat. Further, the carbon nanotube clamping device also includes a third fastener 36, which is used to mount the wire-protecting rubber pad onto the tube clamp seat. The third fastener 36 secures the wire-protecting rubber pad 35 to the front end of the tube clamp seat 33, preventing wear on the wiring harness inside the carbon nanotube assembly 31 by the motor unit 10 and the speed regulating component 20.

[0062] Specifically, please refer to Figure 7 and Figure 8The cable protection pad 35 includes a base plate 351, a symmetrical side clamp assembly 352, and a positioning clamping assembly 353, which are respectively disposed on the base plate 351. The base plate has a plurality of clamping and limiting grooves 354, each clamping and limiting groove being symmetrically disposed on both sides of the base plate. The tube clamp seat 33 has a plurality of limiting protrusions 356, each limiting protrusion correspondingly embedded in one of the clamping and limiting grooves. The symmetrical side clamp assembly includes two side clamping fixing structures 3521, which are respectively used to clamp the left and right side plates 33a of the tube clamp seat 33. The positioning clamping assembly includes two end positioning structures 3531, which are two... The outer clamp fixing component has two positioning channels 357, one above the other, and the two end positioning structures are respectively embedded in the two positioning channels. In one of the end positioning structures, a clamping groove 3532 is also provided. The two clamping grooves are respectively used to clamp the side plate of the top pressing component 3311 and the side plate 33b of the bottom supporting component 3312. In this way, by setting the clamping limiting groove 354 to clamp the limiting protrusion 356, the side clamp fixing structure to clamp the left and right side plates of the pipe clamp seat, and the clamping groove to clamp the side plate of the top pressing component and / or the bottom supporting component, the entire protective pad is fixed on the pipe clamp seat. Then, it is tightened and reinforced by the third fastener 36 to improve the structural reliability.

[0063] It should be noted that the substrate 351, as the foundation of the entire wire protection pad structure, has several clamping and limiting grooves 354 symmetrically distributed on both sides of the substrate, forming an initial constraint on the tube clamp seat 33. In particular, the tube clamp seat 33 is specially designed with multiple limiting protrusions 356, which correspond one-to-one with the clamping and limiting grooves 354, precisely fitting together to achieve a preliminary stable connection and improve the stability of the entire system.

[0064] The symmetrical side clamp assembly 352 further enhances the system's stability through two side clamp fixing structures. These two side clamp fixing structures firmly hold the left and right side plates of the pipe clamp seat 33, ensuring the pipe clamp seat remains stable in the lateral dimension. This symmetrical design not only improves the structural balance but also makes the installation process more convenient and efficient.

[0065] The positioning and clamping assembly 353 provides longitudinal fixation support for the system using two end positioning structures. These two end positioning structures are cleverly embedded within two positioning channels, which are jointly enclosed by the outer clamp fixing members, providing sufficient space while ensuring positioning accuracy. Particularly noteworthy is the clamping groove specially provided on the end positioning structure, which allows the side plates of the top pressing member 3311 and / or the bottom supporting member 3312 to be firmly clamped, thereby achieving further fixation of the pipe clamp seat in the longitudinal direction.

[0066] By combining the clamping and limiting groove 354, the side clamp fixing structure, and the clamping groove, a horizontal and vertical fixing system is formed, firmly fixing the cable protection pad 35 to the pipe clamp seat 33. Furthermore, the addition of the third fastener 36 further enhances the stability of the installation, and by tightening and reinforcing, the reliability and stability of the entire structure are further improved.

[0067] In summary, by incorporating the protective rubber pad 35, not only is the pipe clamp seat 33 fully secured, but the interconnection and interaction between the components also create a stable yet flexible fixing system. This not only improves the reliability of the structure but also facilitates subsequent cable protection and management, ensuring the safe and efficient operation of the UAV.

[0068] Please see Figure 1 and Figure 2 The motor assembly 10 includes two motors, which are symmetrically arranged on the pipe clamp seat. The pipe clamp seat has two motor mounting slots 333, and the two motors are respectively arranged in the two motor mounting slots. The speed regulating component includes two speed regulators, which are symmetrically arranged on the pipe clamp seat. The pipe clamp seat has two speed regulating fixing slots 334, and the two speed regulators are respectively arranged in the two speed regulating fixing slots.

[0069] Please see Figure 3The carbon nanotube clamping device further includes a front sealing cover 40 and a rear sealing cover 50, which are respectively installed on the tube clamp seat. Thus, the front and rear ends of the carbon nanotube clamping device 30 are respectively equipped with the front sealing cover 40 and the rear sealing cover 50, thereby achieving dust and water protection inside the carbon nanotube clamping device 30. To further improve the protective performance of the device, the present invention provides dust and water protection for the carbon nanotube clamping device 30 by setting the front sealing cover 40 and the rear sealing cover 50. The front sealing cover 40 and the rear sealing cover 50 are respectively tightly installed at the front and rear ends of the tube clamp seat, forming a seamless connection with the tube clamp seat, thereby effectively preventing the intrusion of harmful substances such as dust and moisture from the outside. The interaction and connection between the front sealing cover 40, the rear sealing cover 50 and the tube clamp seat not only achieves dust and water protection inside the device, but also greatly improves the stability and durability of the entire power system.

[0070] It should also be noted that the number of the outer clamp fastener 313 and the inner lining fastener 314 is set to 2. The number of the first fastener 312 and the second fastener 34 is set to 8, and the number of the third fastener 36 is set to 8.

[0071] This invention, by setting up a carbon tube and an outer hoop and inner liner fixing component fixed to the carbon tube, effectively increases the friction area and locking ability of the carbon tube by externally pressing the outer hoop and internally tightening the inner liner. This avoids flight accidents caused by the carbon tube spinning during UAV flight, achieving high load capacity and high structural strength. It effectively solves the shortcomings of heavy-load multi-rotor coaxial power kits and largely solves the problems of structural strength and heavy load loading for heavy-load multi-rotor UAVs.

[0072] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this patent should be determined by the appended claims.

Claims

1. A carbon tube clamping device for heavy load multi-rotor unmanned aerial vehicle coaxial power suit, characterized in that, The carbon tube clamping device comprises: a pipe clamp base for mounting a motor set and a speed regulating assembly; a carbon tube assembly mounted on the pipe clamp base, the carbon tube assembly comprising a carbon tube, an outer hoop fixing member and an inner liner fixing member, the inner liner fixing member being mounted on the carbon tube, and the outer hoop fixing member being wrapped on the carbon tube; the carbon tube assembly further comprising a first fastener for fixing the outer hoop fixing member and the inner liner fixing member on the carbon tube respectively; the outer hoop fixing member is provided with two outer hoop fixing members, and the two outer hoop fixing members are respectively sleeved on the carbon tube; in one of the outer hoop fixing members, the outer hoop fixing member is provided with an outer hoop upper and lower limiting part and an outer hoop left and right limiting part, the pipe clamp base is provided with a pipe clamp upper and lower limiting structure matched with the outer hoop upper and lower limiting part, and the pipe clamp base is provided with a pipe clamp left and right limiting structure matched with the outer hoop left and right limiting part.

2. The carbon tube clamping device of the heavy load multi-rotor unmanned aerial vehicle coaxial power suit of claim 1, wherein, The carbon tube clamping device further comprises a gasket mounted on the pipe clamp base, and the gasket is used to fill the gap between the carbon tube assembly and the pipe clamp base.

3. The carbon tube clamping device of the heavy load multi-rotor unmanned aerial vehicle coaxial power suit of claim 2, wherein, The carbon tube clamping device further comprises a second fastener for mounting the gasket on the pipe clamp base.

4. The carbon tube clamping device of the heavy load multi-rotor unmanned aerial vehicle coaxial power suit of claim 1, wherein, The carbon tube clamping device further comprises a wire protection rubber pad mounted on the pipe clamp base.

5. The carbon tube clamping device of the heavy load multi-rotor unmanned aerial vehicle coaxial power suit of claim 4, wherein, The carbon tube clamping device further comprises a third fastener for mounting the wire protection rubber pad on the pipe clamp base.

6. The carbon tube clamping device of the heavy load multi-copter coaxial power suit according to claim 1, wherein, The outer hoop upper and lower limiting part and the outer hoop left and right limiting part are elastically deformable structures.

7. The carbon tube clamping device of the heavy load multi-copter coaxial power suit according to claim 1, wherein, The motor set comprises two motors, and the two motors are respectively and symmetrically arranged on the pipe clamp base, the pipe clamp base is provided with two motor mounting grooves, and the two motors are respectively arranged in the two motor mounting grooves; The speed regulating assembly comprises two speed regulators, and the two speed regulators are respectively and symmetrically arranged on the pipe clamp base, the pipe clamp base is provided with two speed regulating fixing grooves, and the two speed regulators are respectively arranged in the two speed regulating fixing grooves.

8. The carbon tube clamping device of the heavy load multi-copter coaxial power suit according to claim 1, wherein, The carbon tube clamping device further comprises a front sealing cover and a rear sealing cover, and the front sealing cover and the rear sealing cover are respectively mounted on the pipe clamp base.

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