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

Abstract

The invention discloses a heavy-load multi-rotor unmanned aerial vehicle coaxial power sleeving carbon tube clamping device which comprises a tube clamping seat and a carbon tube assembly, and the tube clamping seat is used for installing a motor set and a speed adjusting assembly; the carbon tube assembly is installed on the tube clamping seat, the carbon tube assembly comprises a carbon tube, an outer hoop fixing piece and a lining fixing piece, the lining fixing piece is installed on the carbon tube, and the outer hoop fixing piece wraps the carbon tube. By arranging the carbon tube, and the outer hoop fixing piece and the lining fixing piece which are fixed on the carbon tube, that is, the friction area and the locking capacity of the carbon tube can be effectively improved by pressing the outer hoop from the outside and tensioning the lining from the inside, so that flight accidents caused by rotation of the carbon tube in the flight process of the unmanned aerial vehicle are avoided, and the safety of the unmanned aerial vehicle is improved. Large load and high structural strength are achieved, the defect of heavy-load multi-rotor coaxial power sleeving is effectively overcome, and the problems of structural strength and large-load loading of the heavy-load multi-rotor unmanned aerial vehicle are solved to a great extent.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a carbon tube clamping device for a coaxial power suit of a heavy-loaded multi-rotor unmanned aerial vehicle. Background Art

[0002] Heavy-load multi-rotor drones are an important trend in the current development of industrial drones. They have excellent load-bearing capacity and stable flight characteristics, and are suitable for a variety of scenarios, including logistics transportation, emergency rescue, military reconnaissance, etc. However, most of the heavy-load multi-rotor drones on the market currently use single-axis motors as power output, or the existing coaxial power sets are light in weight and do not meet the requirements of large carrying capacity. Summary of the invention

[0003] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a carbon tube clamping device for a heavy-loaded multi-rotor UAV coaxial power suit, which achieves large load and high structural strength, effectively solves the shortcomings of the heavy-loaded multi-rotor coaxial power suit, and to a large extent solves the problems of structural strength and large load loading of heavy-loaded multi-rotor UAVs.

[0004] The objective of the present invention is achieved through the following technical solutions:

[0005] A carbon tube clamping device for a coaxial power suit of a heavy-loaded multi-rotor UAV comprises: a tube clamp seat and a carbon tube assembly,

[0006] The pipe clamp seat is used to install the motor group and the speed regulating component;

[0007] The carbon tube assembly is installed on the tube clamp seat, and the carbon tube assembly includes a carbon tube, an outer hoop fixing part and an inner lining fixing part, the inner lining fixing part is installed on the carbon tube, and the outer hoop fixing part is wrapped on the carbon tube.

[0008] In one embodiment, the carbon tube assembly further includes a first fastener, and the first fastener is used to fix the outer hoop fixing member and the inner liner fixing member to the carbon tube respectively.

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

[0010] In one embodiment, the carbon tube clamping device further includes a second fastener, and the second fastener is used to install the gasket on the tube clamp seat.

[0011] In one of the embodiments, the carbon tube clamping device further includes a wire protection rubber pad, and the wire protection rubber pad is installed on the tube clamp seat.

[0012] In one of the embodiments, the carbon tube clamping device further includes a third fastener, and the third fastener is used to install the wire protection pad on the tube clamp seat.

[0013] In one embodiment, two outer hoop fixing members are provided, and the two outer hoop fixing members are respectively sleeved on the carbon tube;

[0014] In one of the outer hoop fixings, the outer hoop fixing is provided with an outer hoop upper and lower limiting portion and an outer hoop left and right limiting portion, the tube clamp seat is provided with a tube clamp upper and lower limiting structure cooperating with the outer hoop upper and lower limiting portions, and the tube clamp seat is provided with a tube clamp left and right limiting structure cooperating with the outer hoop left and right limiting portions.

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

[0016] In one embodiment, the motor group includes two motors, the two motors are symmetrically arranged on the pipe clamp seat, the pipe clamp seat is provided with two motor mounting grooves, and the two motors are correspondingly arranged in the two motor mounting grooves;

[0017] The speed regulating assembly comprises two speed regulators, which are symmetrically arranged on the pipe clamp seat, and the pipe clamp seat is provided with two speed regulating fixing grooves, and the two speed regulators are correspondingly arranged in the two speed regulating fixing grooves.

[0018] In one embodiment, 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 installed on the tube clamp seat.

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

[0020] The present invention is a carbon tube clamping device for a coaxial power suit of a heavy-loaded multi-rotor unmanned aerial vehicle. By setting a carbon tube, and an outer hoop fixing member and an inner liner fixing member fixed on the carbon tube, that is, by externally pressing the outer hoop and internally tightening the inner liner, the friction area and locking ability of the carbon tube can be effectively improved, thereby avoiding flight accidents caused by the carbon tube spinning during the flight of the unmanned aerial vehicle, achieving large load and high structural strength, effectively solving the shortcomings of the heavy-loaded multi-rotor coaxial power suit, and solving the problems of structural strength and large load loading of heavy-loaded multi-rotor unmanned aerial vehicles to a large extent. The structure of the present invention is safe and reliable, and can ensure the safety and stability of the unmanned aerial vehicle during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic structural diagram of a carbon tube clamping device of a coaxial power suit of a heavy-loaded multi-rotor UAV according to an embodiment of the present invention;

[0022] Figure 2 for Figure 1 A structural schematic diagram of a carbon tube clamping device of a coaxial power suit of a heavy-duty multi-rotor UAV from another perspective is shown;

[0023] Figure 3 for Figure 1 A structural schematic diagram of a carbon tube clamping device of a coaxial power suit of a heavy-duty multi-rotor UAV is shown from another perspective;

[0024] Figure 4 for Figure 1 The exploded structural diagram of the carbon tube clamping device of the coaxial power suit of the heavy-loaded multi-rotor UAV shown;

[0025] Figure 5 for Figure 1 A schematic structural diagram of a carbon tube assembly of a carbon tube clamping device shown;

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

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

[0028] Figure 8 for Figure 1 A schematic structural diagram of a wire protection rubber pad of a carbon tube clamping device is shown. DETAILED DESCRIPTION

[0029] In order to facilitate the understanding of the present invention, the present invention will be described more fully below with reference to the relevant drawings. The preferred embodiments of the present invention are given in the drawings. However, the present invention can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present invention more thoroughly understood.

[0030] See also Figure 1 to Figure 4 , a carbon tube clamping device 30 for a heavy-loaded multi-rotor UAV coaxial power suit. 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 capacity and structural stability of traditional heavy-loaded multi-rotor coaxial power suits, and provides a powerful and effective solution for performance optimization and structural strengthening of heavy-loaded multi-rotor UAVs.

[0031] Furthermore, the carbon tube clamping device 30 includes: a tube clamp seat 33 and a carbon tube assembly 31, and the tube clamp seat 33 is used to install the motor group 10 and the speed regulating assembly 20. As the supporting structure of the entire device, the tube clamp seat 33 can not only provide a stable installation platform for the motor group and the speed regulating assembly, ensuring the accuracy and efficiency of power transmission, but also provide a solid and reliable support foundation for the carbon tube assembly through its structural design, ensuring stability and durability under high load and heavy load operation. The carbon tube assembly is mainly composed of three parts: carbon tube, outer hoop fixing and inner lining fixing, which together constitute the key load-bearing unit in the drone structure.

[0032] It should be noted that the carbon tube assembly 31 is installed on the tube clamp seat 33, and the carbon tube assembly 31 includes a carbon tube 311, an outer hoop fixing part 313 and an inner lining fixing part 314, the inner lining fixing part is installed on the carbon tube, and the outer hoop fixing part is wrapped on the carbon tube. The carbon tube 311, with its light weight, high strength and corrosion resistance, is used as the main structural support material, which effectively reduces the overall weight of the drone while ensuring sufficient structural strength and rigidity. The inner lining fixing part 314 fits tightly on the outer wall of the carbon tube, which can effectively enhance the torsion resistance and axial stability of the carbon tube, and effectively prevent deformation or damage caused by long-term heavy-load use. The outer hoop fixing part 313 is installed on the outside of the carbon tube, and through the locking mechanism, it forms a double reinforcement with the inner lining fixing part, further improving the radial strength and overall stability of the carbon tube. The design of the outer hoop fixing part also takes into account the needs of easy installation and disassembly, ensuring the convenience of maintenance and replacement.

[0033] The interaction and connection between the structures are close and efficient. The tube clamp provides a stable support frame for the carbon tube assembly, and the carbon tube assembly achieves all-round and multi-level reinforcement of the carbon tube through the synergy of the lining fixture and the outer hoop fixture, thus ensuring the excellent performance and long-term reliability of the entire device in a high-intensity, high-load working environment. This not only improves the carrying capacity of the drone, but also makes the structure of the heavy-load multi-rotor drone simpler and more reliable.

[0034] In this example, see Figure 5 and Figure 6 , two outer hoop fixing members 313 are provided, and the two outer hoop fixing members 313 are respectively sleeved on the carbon tube 311. Further, the inner side walls of the two outer hoop fixing members jointly form a clamping outer large circle, and two inner liner fixing members 314 are provided, and the two inner liner fixing members 314 are respectively installed on the carbon tube 311. The outer side walls of the two inner liner fixing members jointly form a clamping outer inner circle, and the clamping outer large circle and the clamping outer inner circle jointly form a carbon tube clamping area, and the carbon tube is clamped and fixed in the carbon tube clamping area.

[0035] Furthermore, in one of the outer hoop fixing members, the outer hoop fixing member includes a first outer hoop fixing frame 313a and a second outer hoop fixing frame 313b, and the first outer hoop fixing frame and the second outer hoop fixing frame are an integrally formed structure; the first outer hoop fixing frame is provided with a first avoidance cavity 313a-1 and two first outer hoop fixing holes, and the two first outer hoop fixing holes are connected to the first avoidance cavity together, and the second outer hoop fixing frame is provided with a second avoidance cavity 313b-1 and two second outer hoop fixing holes, and the two second outer hoop fixing holes are connected to the second avoidance cavity together; wherein, the first avoidance cavity and the second avoidance cavity are used to achieve avoidance and facilitate users to install and disassemble.

[0036] It should be noted that the first outer hoop fixing frame 313a and the second outer hoop fixing frame 313b are manufactured by one-piece molding technology, which not only ensures the durability of the structure, but also greatly improves the precision and efficiency of manufacturing. The first outer hoop fixing frame 313a is provided with a first avoidance cavity 313a-1 and two precisely positioned first outer hoop fixing holes. These two fixing holes are connected to the avoidance cavity to form a spatial layout that is easy to install and maintain. Similarly, the second outer hoop fixing frame 313b is also equipped with a second avoidance cavity 313b-1 and two corresponding second outer hoop fixing holes. Such a design not only optimizes the installation process, but also significantly enhances the flexibility and user-friendliness of the structure.

[0037] In another outer hoop fixing part, it includes a third outer hoop fixing frame 313c and a fourth outer hoop fixing frame 313d, and the third outer hoop fixing frame and the fourth outer hoop fixing frame are an integrally formed structure; the third outer hoop fixing frame is provided with a third avoidance cavity 313c-1 and two third outer hoop fixing holes, and the two third outer hoop fixing holes are connected to the third avoidance cavity; the fourth outer hoop fixing frame is provided with a fourth avoidance cavity 313d-1 and two fourth outer hoop fixing holes, and the two fourth outer hoop fixing holes are connected to the fourth avoidance cavity. The third avoidance cavity and the fourth avoidance cavity are used to achieve avoidance and facilitate users to install and disassemble.

[0038] It should be noted that the other outer hoop fixing member is composed of a third outer hoop fixing frame 313c and a fourth outer hoop fixing frame 313d, which are closely connected through advanced one-piece molding technology, which not only ensures the integrity and strength of the structure, but also significantly improves the manufacturing efficiency and precision. This design not only reflects the maximum utilization of material properties, but also improves the structural strength. A third avoidance cavity 313c-1 is provided on the third outer hoop fixing frame 313c, which not only optimizes the installation space, but also provides a more convenient assembly path for users. At the same time, two precisely positioned third outer hoop fixing holes are connected to the third avoidance cavity, forming a transfer area that is both stable and flexible. Similarly, the fourth outer hoop fixing frame 313d is also equipped with a corresponding fourth avoidance cavity 313d-1 and two fourth outer hoop fixing holes. Such a layout not only enhances the flexibility of the structure, but also significantly improves the convenience of installation and maintenance.

[0039] In this embodiment, the carbon tube is provided with a first connecting hole, a second connecting hole, a third connecting hole, and a fourth connecting hole, which are arranged around the carbon tube, and two of each of the first connecting hole, the second connecting hole, the third connecting hole, and the fourth connecting hole is arranged. It should be noted that four groups of connecting holes are evenly arranged around the carbon tube - the first connecting hole, the second connecting hole, the third connecting hole, and the fourth connecting hole, and each group includes two holes. Such a layout not only optimizes the force distribution of the structure, but also provides a precise positioning point for subsequent fixed connection.

[0040] Furthermore, in one of the lining fixing parts 314, the lining fixing part includes a first lining fixing piece 314a and a second lining fixing piece 314b, the first lining fixing piece and the second lining fixing piece are an integrally formed structure, the first lining fixing piece is provided with two first lining fixing holes, and the second lining fixing piece is provided with two second lining fixing holes. It should be noted that one of the lining fixing parts 314 is composed of a first lining fixing piece 314a and a second lining fixing piece 314b, and the two parts are interconnected by an integral forming technology to form a whole that is both strong and flexible. The first lining fixing piece 314a is provided with two first lining fixing holes, and the second lining fixing piece 314b is provided with two second lining fixing holes, which not only provide precise docking points for subsequent fastening operations, but also significantly enhance the stability and durability of the structure.

[0041] In another of the lining fixing parts, it includes a third lining fixing piece 314c and a fourth lining fixing piece 314d, and the third lining fixing piece and the fourth lining fixing piece are an integrally formed structure, and the third lining fixing piece is provided with two third lining fixing holes, and the fourth lining fixing piece is provided with two fourth lining fixing holes. In this way, the other lining fixing part is composed of the third lining fixing piece 314c and the fourth lining fixing piece 314d, and these two parts also adopt an integrally formed structure, which ensures the integrity of the structure and improves the hardness and strength. The third lining fixing piece 314c is provided with two third lining fixing holes, and the fourth lining fixing piece 314d is also provided with two fourth lining fixing holes, which can improve the flexibility and adaptability of the structure.

[0042] It should be noted that the first avoidance 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 plate are interconnected to form a first fixed cavity 312a. After the first fastener 312 is penetrated into the first fixed cavity, the first outer hoop fixing frame, the carbon tube, and the first inner lining fixing plate are connected and fixed; the second avoidance 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 plate are interconnected to form a second fixed cavity 312b. After the first fastener 312 is set in the second fixed cavity, the second outer hoop fixing frame, the carbon tube, and the fourth inner lining fixing plate are connected and fixed. The third avoidance cavity and the third outer hoop fixing hole of the third outer hoop fixing frame, the third connecting hole on the carbon tube, and the third inner lining fixing hole of the third inner lining fixing plate are connected to each other to form a third fixed cavity 312c. After the first fastener 312 is set in the third fixed cavity, the third outer hoop fixing frame, the carbon tube, and the third inner lining fixing plate are connected and fixed; the fourth avoidance cavity and the fourth outer hoop fixing hole of the fourth outer hoop fixing frame, the fourth connecting hole on the carbon tube, and the second inner lining fixing hole of the second inner lining fixing plate are connected to each other to form a fourth fixed cavity 312d. After the first fastener 312 is set in the fourth fixed cavity, the fourth outer hoop fixing frame, the carbon tube, and the second inner lining fixing plate are connected and fixed.

[0043] Specifically, the first avoidance cavity on the first outer hoop fixing frame and the first outer hoop fixing hole, the first connecting hole arranged on the carbon tube, and the first liner fixing hole on the first liner fixing plate are interconnected, and together form a precise first fixing cavity 312a. When the first fastener 312 passes through this cavity, it firmly connects the first outer hoop fixing frame, the carbon tube and the first liner fixing plate together, forming a fixing system that is both tight, stable and reliable.

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

[0045] In the internal structure of the drone frame, the first lining fixing plate and the second lining fixing plate ensure the integrity and stability of the structure through one-piece molding technology. The two lining fixing plates are respectively provided with fixing holes that match the connecting holes at specific positions on the carbon tube, providing precise docking and fixing points for subsequent fixing operations. In the overall layout of the drone carbon tube fixing frame, these outer hoop fixing frames are connected to the specific connecting holes on the carbon tube and the fixing holes on the lining fixing parts through the fixing holes thereon, together 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 tube and the fixing holes on the lining fixing parts) form an independent fixed cavity, while the fourth outer hoop fixing frame and its supporting components constitute another complementary fixed cavity. By penetrating these fixed cavities with the first fasteners (such as bolts, screws, etc.), a firm and stable connection is established between the outer hoop fixing parts, the carbon tubes and the lining fixing parts. This design not only achieves a tight connection of the structure, but also significantly improves the friction area and locking ability between the carbon tube and the fixings through the compression of the outer hoop fixings and the tension of the inner lining fixings. This double locking mechanism not only enhances the overall stability of the structure, but also effectively avoids the loosening or deformation of the structure that may occur during high-speed flight of the drone, thereby ensuring the safety and reliability of the flight.

[0046] In the drone system, a connection is established between the inner lining fixing piece, the outer hoop fixing piece and the carbon tube. Specifically, the fixing holes on the first inner lining fixing piece and the second inner lining fixing piece correspond to the first connecting hole and the second connecting hole on the carbon tube, respectively. By penetrating these holes with fasteners, a firm connection is established between the inner lining fixing piece and the carbon tube. Similarly, the third inner lining fixing piece and the fourth inner lining fixing piece cooperate with the third connecting hole and the fourth connecting hole on the carbon tube to form another independent fixing system.

[0047] Furthermore, the carbon tube assembly also includes a first fastener 312, which is used to fix the outer hoop fixing member and the inner liner fixing member to the carbon tube respectively. The first fastener 312 serves as a locking component for connection and fixing, which can ensure the close fit and reliable fixation between the various components of the carbon tube assembly. This not only improves the overall stability of the structure, but also significantly enhances the reliability of the heavy-loaded multi-rotor drone when facing extreme conditions.

[0048] Specifically, the first fastener 312 acts on the reinforcement process of the carbon tube assembly. The first fastener 312 is arranged between the outer hoop fixing member and the carbon tube. Through the tightening process, the screw of the first fastener generates a strong radial pressure, which presses the outer hoop fixing member tightly and evenly on the outer surface of the carbon tube. This not only enhances the radial support force of the carbon tube, but also effectively prevents loosening caused by vibration or external force, ensuring the structural integrity of the carbon tube assembly under long-term, high-load operation. The outer hoop fixing member and the inner liner fixing member complement each other, and the first fastener 312 simultaneously tightens the inner liner fixing member firmly on the carbon tube. By setting the first fastener 312, the inner liner fixing member is tightly attached to the carbon tube, forming an additional protective layer, which effectively improves the torsional strength and axial stability of the carbon tube. In addition, the inner liner fixing member ensures that the carbon tube assembly can still maintain good structural performance under different ambient temperatures according to the thermal expansion and contraction characteristics of the carbon tube. The first fastener 312 not only achieves a firm connection between the components of the carbon tube assembly through physical fastening, but also optimizes the stress state of the carbon tube through evenly distributed pressure and tension, thereby significantly improving the bearing capacity and structural strength of the entire carbon tube assembly.

[0049] In this way, by setting the carbon tube, and the outer hoop fixing part and the inner liner fixing part fixed on the carbon tube, that is, by externally pressing the outer hoop and internally tightening the inner liner, the friction area and locking ability of the carbon tube can be effectively improved, thereby avoiding flight accidents caused by the carbon tube spinning during the flight of the drone, achieving large load and high structural strength, effectively solving the shortcomings of the heavy-loaded multi-rotor coaxial power suit, and solving the structural strength and large load loading problems of the heavy-loaded multi-rotor drone to a large extent. The structure of the present invention is safe and reliable, and can ensure the safety and stability of the drone during flight.

[0050] See also Figure 4, the carbon tube clamping device also includes a gasket 32, which is installed on the tube clamp seat, and the gasket is used to fill the gap between the carbon tube assembly and the tube clamp seat. Further, the carbon tube clamping device also includes a second fastener 34, and the second fastener is used to install the gasket on the tube clamp seat. In this way, the gasket 32 ​​is used to fill the gap caused by the assembly of the carbon tube assembly 31 and the tube clamp seat 33, and the second fastener 34 fixes the gasket 32 ​​in the tube clamp seat 33. Among them, the gasket 32 ​​is an optional item, which is used to fill the gap caused by the processing accuracy of each component. The number is not limited to 2. Optionally, the number of gaskets 32 used is multiple or even zero.

[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 the seamless connection between the carbon tube assembly and the tube clamp seat. The gasket 32 ​​is installed between the tube clamp seat and the carbon tube assembly. Its main function is to fill the small gap between the two, thereby eliminating potential assembly errors and tolerance accumulation, and 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 the loosening or damage of the components caused by vibration or long-term stress concentration. The material is selected from high-strength, wear-resistant and elastic materials to ensure that the gasket can continue to provide stable support and buffering in a complex and changeable flight environment. The second fastener 34 is the key link between the gasket 32 ​​and the tube clamp seat. The second fastener 34 can be in the form of a high-strength screw or bolt. After tightening, the gasket is firmly fixed on the tube clamp seat, thereby ensuring a close fit and stable connection between the carbon tube assembly and the tube clamp seat. The installation of the second fastener can ensure 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 act together between the carbon tube assembly and the tube clamp seat, and by filling the gap and applying the fastening force, a seamless connection and efficient coordination between the two are achieved. This not only improves the overall stability and durability of the carbon tube clamping device, but also provides a more reliable structural support for heavy-loaded multi-rotor drones in the face of complex flight conditions.

[0052] The wire protection pad 35 has the characteristics of soft and elastic material, and can fit tightly to the front end of the tube clamp seat 33. The main function of the wire protection pad 35 is to provide an additional protective layer for the wiring harness of the motor group 10 and the speed control assembly 20 passing through the carbon tube assembly 31. It can effectively absorb vibration and buffer shock, thereby preventing the wiring harness from being worn due to long-term friction or external force, ensuring the integrity of the wiring harness and the stability of signal transmission. The third fastener 36 is used as a fixing member connecting the wire protection pad 35 and the tube clamp seat 33. The third fastener 36 is in the form of a high-strength screw or bolt. After tightening, the wire protection pad 35 can be firmly fixed to the front end of the tube clamp seat 33. This not only ensures the close fit between the wire protection pad 35 and the tube clamp seat 33, but also prevents the displacement of the wire protection pad under vibration or external force by applying appropriate tightening force, thereby ensuring the long-term stability and reliability of the wiring harness protection system. In this way, the interaction and connection relationship between the wire protection pad 35 and the third fastener 36 constitute an external wiring harness protection system. They work together on the carbon tube clamping device, and by providing an additional protective layer and applying a tightening force, effectively prevent the wiring harness of the motor group 10 and the speed regulating assembly 20 from being worn inside the carbon tube assembly 31. This not only improves the overall stability and durability of the UAV power system, but also provides a more solid guarantee for the safe flight of the UAV.

[0053] In the present embodiment, in one of the outer hoop fixing members 313, the outer hoop fixing member is provided with an outer hoop upper and lower limit portion 3131 and an outer hoop left and right limit portion 3132, the tube clamp seat 33 is provided with a tube clamp upper and lower limit structure 331 that cooperates with the outer hoop upper and lower limit portions, and the tube clamp seat is provided with a tube clamp left and right limit structure 332 that cooperates with the outer hoop left and right limit portions. In the present embodiment, the outer hoop upper and lower limit portions and the outer hoop left and right limit portions are both elastically deformable structures. In this way, the outer hoop upper and lower limit portions 3131 and the outer hoop left and right limit portions 3132 are processed into a shape with elastic deformation, and the tube clamp seat 33 and the carbon tube assembly 31 are limitedly assembled, which can effectively avoid the deformation and resonance caused by the yaw of the drone during flight.

[0054] In the carbon tube clamping device structure of the coaxial power suit of the heavy-loaded multi-rotor UAV, by setting the upper and lower limit parts 3131 of the outer hoop and the left and right limit parts 3132 of the outer hoop on the outer hoop fixing member, and the upper and lower limit structures 331 of the tube clamp and the left and right limit structures 332 of the tube clamp on the tube clamp seat 33, which cooperate with each other, not only greatly improve the stability of the device, but also effectively suppress the deflection, deformation and resonance phenomena during the flight of the UAV. The upper and lower limit parts 3131 of the outer hoop and the left and right limit parts 3132 of the outer hoop both adopt an elastically deformable structure, which means that they can be deformed and adjusted to a certain extent according to the actual needs during the installation process to adapt to the cooperation and swing 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 that a tight and stable connection can be formed between the limit part and the limit structure, effectively preventing the loosening of components caused by vibration or external force. The upper and lower limit structures 331 of the tube clamp and the left and right limit structures 332 of the tube clamp can ensure the cooperation with the upper and lower limit parts 3131 of the outer hoop and the left and right limit parts 3132 of the outer hoop by setting two structures. Not only does it provide the necessary limit function, but also provides additional support and protection for the carbon tube assembly 31 through its own structure. When the outer hoop fixing part and the tube clamp seat 33 are tightly connected through the cooperation of the limit part and the limit structure, the entire carbon tube clamping device forms a stable and reliable framework, providing a solid foundation for the safe operation of the UAV power system.

[0055] For further information, see Figure 7The upper and lower limiting structures 331 of the pipe clamp include a top pressing piece 3311 and a bottom supporting piece 3312, and the top pressing piece and the bottom supporting piece are used to act together on the outer hoop fixing piece, that is, the top pressing piece and the bottom supporting piece are used to clamp the two outer hoop fixing pieces; specifically, the top pressing piece is used to press on the top of the upper and lower limiting parts of the outer hoop of the two outer hoop fixing pieces, and the bottom supporting piece is used to support the bottom of the upper and lower limiting parts of the outer hoop of the two outer hoop fixing pieces. At the same time, the left and right limiting structures 332 of the tube clamp include a left clamping piece 3321 and a right clamping piece 3322, and the left clamping piece and the right clamping piece are used to act on the outer hoop fixing piece together, that is, the left clamping piece and the right clamping piece are used to clamp the two outer hoop fixing pieces; specifically, the left clamping piece is used to press on the outer side wall of one of the outer hoop fixing pieces, and the right clamping piece is used to press on the relative position of the outer side wall of the other outer hoop fixing piece. In this way, through the top pressing piece 3311, the bottom supporting piece 3312, the left clamping piece 3321 and the right clamping piece 3322, the two outer hoop fixing pieces can be clamped and fixed more firmly, and the position of the carbon tube can be further fixed, which can effectively avoid deformation and resonance caused by the yaw of the drone during flight. In addition, since the top pressing member 3311, the bottom supporting member 3312, the left clamping member 3321 and the right clamping member 3322 are configured to have elastically deformable shapes, the resonance of the drone during flight can be filtered out more effectively.

[0056] It should also be noted that the positioning structure system of the tube clamp integrates a dual stabilization mechanism of up and down and left and right, specifically, an upper and lower positioning structure 331 composed of a top pressing member 3311 and a bottom holding member 3312, and a left and right positioning structure 332 composed of a left clamping member 3321 and a right clamping member 3322. These two structures work together to accurately and firmly fix the outer hoop fixing member, thereby ensuring that the position of the carbon tube is stable and secure.

[0057] In the upper and lower limiting structures 331, the top pressing member 3311 can accurately press on the top of the upper and lower limiting parts of the two outer hoop fixing members, which can effectively prevent the upward movement tendency caused by external force or vibration. The bottom supporting member 3312 is firmly supported on the bottom of the upper and lower limiting parts of the two outer hoop fixing members, forming a stable support, effectively resisting downward pressure and possible deformation. The two complement each other, ensuring the stability in the vertical direction, and through their close cooperation, significantly improving the rigidity of the overall structure.

[0058] At the same time, the left and right limiting structures 332 are arranged on the left and right sides, further strengthening the overall stability. The left clamping piece 3321 is tightly fitted to the outer side wall of one of the outer hoop fixings, and through its tight wrapping and pressure, it effectively prevents the lateral displacement of the side wall. The right clamping piece 3322 is pressed against the relative position of the outer side wall of the other outer hoop fixing, ensuring that the two are tightly fitted in the horizontal direction, thereby forming another solid limiting structure in the horizontal direction. The close cooperation between the two not only ensures the stability in the left and right directions, but also effectively suppresses any possible distortion or deformation through its uniform clamping force.

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

[0060] To sum up, through the limiting structural system of the top pressing piece 3311, the bottom supporting piece 3312, the left clamping piece 3321 and the right clamping piece 3322, the two outer hoop fixing parts are firmly and stably clamped and fixed, and the position of the carbon tube is precisely controlled, which not only enhances the structural strength and stability of the UAV, but also effectively avoids deformation and resonance problems caused by factors such as yaw and vibration during flight, thereby improving the safety and efficiency of the UAV.

[0061] See also Figure 4 The carbon tube clamping device further includes a wire protection rubber pad 35, which is installed on the tube clamp seat. Further, the carbon tube clamping device further includes a third fastener 36, which is used to install the wire protection rubber pad on the tube clamp seat. The third fastener 36 fixes the wire protection rubber pad 35 to the front end of the tube clamp seat 33 to prevent the wiring harness of the motor group 10 and the speed regulating assembly 20 from being worn inside the carbon tube assembly 31.

[0062] Specifically, see Figure 7 and Figure 8The wire protection pad 35 includes a base plate 351, a symmetrical side clamp assembly 352 and a positioning clamp assembly 353, and the symmetrical side clamp assembly 352 and the positioning clamp assembly 353 are respectively arranged on the base plate 351; a plurality of clamping limit grooves 354 are arranged on the base plate, and each of the clamping limit grooves is symmetrically arranged on both sides of the base plate, and a plurality of limit ribs 356 are arranged on the pipe clamp seat 33, and each of the limit ribs is respectively embedded in one of the clamping limit grooves; the symmetrical side clamp assembly includes two side clamp fixing structures 3521, and the two side clamp fixing structures are respectively used to clamp the left and right side plates 33a of the pipe clamp seat 33, and the positioning clamp assembly includes two end positioning structures 3531, and the two end positioning structures 3532 ... There are two upper and lower positioning channels 357 between the outer hoop fixing parts, and the two end positioning structures are respectively embedded in the two positioning channels; and in one of the end positioning structures, a clamping groove 3532 is also provided on the end positioning structure, and the two clamping grooves are respectively used to clamp the side plate body 33b of the top pressing part 3311 and the bottom supporting part 3312. In this way, the clamping limit groove 354 is set to clamp the limiting ridge 356, the side clamp fixing structure clamps the left and right side plates of the pipe clamp seat, and the clamping groove clamps the side plate body of the top pressing part and / or the bottom supporting part, so that the entire wire protection pad is fixed on the pipe clamp seat, and then tightened and reinforced by the third fastener 36 to improve the structural reliability.

[0063] It should be noted that the base plate 351, as the basis of the entire wire protection rubber pad structure, is provided with a plurality of clamping limit grooves 354, which are symmetrically distributed on both sides of the base plate, forming a preliminary constraint on the pipe clamp seat 33. In particular, the pipe clamp seat 33 is specially designed with a plurality of limit ridges 356, which correspond to the clamping limit grooves 354 one by one, and are precisely fitted, thereby achieving a preliminary stable connection and improving the stability of the entire system.

[0064] The symmetrical side clamp assembly 352 further enhances the stability of the system through two side clamp fixing structures. The two side clamp fixing structures respectively tightly clamp the left and right side plates of the pipe clamp seat 33, ensuring that the pipe clamp seat is stable in the horizontal dimension. This symmetrical design not only improves the balance of the structure, but also makes the installation process more convenient and efficient.

[0065] The positioning clamping assembly 353 provides longitudinal fixed support for the system with two end positioning structures. The two end positioning structures are cleverly embedded in two positioning channels, which are surrounded by the outer hoop fixing parts, providing sufficient space and ensuring the accuracy of positioning. It is particularly worth mentioning that the end positioning structure is also specially provided with a clamping groove, which enables the side plate of the top pressing member 3311 and / or the side plate of the bottom supporting member 3312 to be firmly clamped, thereby further fixing the pipe clamp seat in the longitudinal direction.

[0066] By setting the clamping limit groove 354, the side clamp fixing structure and the clamping groove, a horizontal and vertical fixing system is formed to firmly fix the wire protection pad 35 on the pipe clamp seat 33. On this basis, the addition of the third fastener 36 further strengthens the stability of its installation, and by tightening and reinforcing, the reliability and stability of the entire structure are further improved.

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

[0068] See also Figure 1 and Figure 2 The motor group 10 includes two motors, and the two motors are symmetrically arranged on the pipe clamp seat. The pipe clamp seat is provided with two motor mounting grooves 333, and the two motors are respectively correspondingly arranged in the two motor mounting grooves; the speed regulation assembly includes two speed regulators, and the two speed regulators are respectively symmetrically arranged on the pipe clamp seat. The pipe clamp seat is provided with two speed regulation fixing grooves 334, and the two speed regulators are respectively correspondingly arranged in the two speed regulation fixing grooves.

[0069] See also Figure 3, the carbon tube clamping device also includes a front sealing cover 40 and a rear sealing cover 50, and the front sealing cover and the rear sealing cover are respectively installed on the tube clamp seat. In this way, the front and rear ends of the carbon tube clamping device 30 are respectively equipped with the front sealing cover 40 and the rear sealing cover 50, so as to realize the dustproof and waterproof inside the carbon tube clamping device 30. In order to further improve the protection performance of the device, the present invention provides dustproof and waterproof functions for the carbon tube 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, and a seamless connection is formed between them and 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 realizes the dustproof and waterproof protection of the inside of 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 hoop fixing member 313 and the inner lining fixing member 314 is set to 2. The number of the first fasteners 312 and the second fasteners 34 is set to 8, and the number of the third fasteners 36 is set to 8.

[0071] The present invention can effectively improve the friction area and locking ability of the carbon tube by arranging a carbon tube, and an outer hoop fixing part and an inner liner fixing part fixed on the carbon tube, that is, by externally pressing the outer hoop and internally tightening the inner liner, thereby avoiding flight accidents caused by the carbon tube spinning during the flight of the unmanned aerial vehicle, achieving large load and high structural strength, effectively solving the shortcomings of the heavy-loaded multi-rotor coaxial power suit, and solving the problems of structural strength and large load loading of the heavy-loaded multi-rotor unmanned aerial vehicle to a large extent.

[0072] The above-mentioned embodiments only express several embodiments of the present invention, and the description is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent of the present invention. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.

Claims

1. A carbon tube clamping device for a coaxial power suit of a heavy-loaded multi-rotor UAV, characterized in that: include: A pipe clamp seat, which is used to install the motor unit and the speed regulating component; A carbon tube assembly is installed on the tube clamp seat, the carbon tube assembly comprises a carbon tube, an outer hoop fixing part and an inner lining fixing part, the inner lining fixing part is installed on the carbon tube, and the outer hoop fixing part is wrapped on the carbon tube.

2. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 1 is characterized in that: The carbon tube assembly further includes a first fastener, which is used to fix the outer hoop fixing member and the liner fixing member to the carbon tube respectively.

3. The carbon tube clamping device of the coaxial power suit of the heavy-loaded multi-rotor UAV according to claim 1 is characterized in that: The carbon tube clamping device further comprises a gasket, which is mounted on the tube clamp seat and is used to fill the gap between the carbon tube assembly and the tube clamp seat.

4. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 3 is characterized in that: The carbon tube clamping device further comprises a second fastener, and the second fastener is used for mounting the gasket on the tube clamp seat.

5. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 1 is characterized in that: The carbon tube clamping device also includes a wire protection rubber pad, which is installed on the tube clamp seat.

6. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 5 is characterized in that: The carbon tube clamping device also includes a third fastener, and the third fastener is used to install the wire protection rubber pad on the tube clamp seat.

7. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 1 is characterized in that: The outer hoop fixing members are provided with two, and the two outer hoop fixing members are respectively sleeved on the carbon tube; In one of the outer hoop fixings, the outer hoop fixing is provided with an outer hoop upper and lower limiting portion and an outer hoop left and right limiting portion, the tube clamp seat is provided with a tube clamp upper and lower limiting structure cooperating with the outer hoop upper and lower limiting portions, and the tube clamp seat is provided with a tube clamp left and right limiting structure cooperating with the outer hoop left and right limiting portions.

8. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 7 is characterized in that: The upper and lower limiting parts of the outer hoop and the left and right limiting parts of the outer hoop are all elastically deformable structures.

9. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 1 is characterized in that: The motor group includes two motors, the two motors are symmetrically arranged on the pipe clamp seat, the pipe clamp seat is provided with two motor mounting grooves, and the two motors are correspondingly arranged in the two motor mounting grooves; The speed regulating assembly comprises two speed regulators, which are symmetrically arranged on the pipe clamp seat, and the pipe clamp seat is provided with two speed regulating fixing grooves, and the two speed regulators are correspondingly arranged in the two speed regulating fixing grooves.

10. The carbon tube clamping device for the coaxial power suit of a heavy-loaded multi-rotor UAV according to claim 1, characterized in that: 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 installed on the tube clamp seat.

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