A power system of a multi-rotor unmanned aerial vehicle

Abstract

The application relates to a power system of a multi-rotor unmanned aerial vehicle, which comprises a pipe clamp seat, a carbon pipe mounting seat mounted in the outer shell of the pipe clamp seat, a carbon pipe inner support, a carbon pipe and a motor. The carbon pipe mounting seat is provided with a hollow mounting through hole. The carbon pipe inner support comprises an inner support pipe body and a horizontal positioning boss connected to the outer side of the inner support pipe body. The horizontal positioning boss is connected with the carbon pipe mounting seat, so that an assembly gap is formed between the inner support pipe body and the mounting through hole. The carbon pipe is provided with a horizontal positioning groove at the end, is inserted into the assembly gap, and the horizontal positioning groove is clamped with the horizontal positioning boss. After the carbon pipe mounting seat, the carbon pipe inner support and the carbon pipe are connected, the carbon pipe is clamped by the carbon pipe mounting seat and the carbon pipe inner support. The motor is connected to the side of the pipe clamp seat. The application can increase the stress area of the carbon pipe, make the stress of the carbon pipe uniform, and eliminate the phenomenon of carbon pipe explosion.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a power system for a multi-rotor UAV. Background Technology

[0002] In multi-rotor drones, each rotor is typically connected to the fuselage via carbon fiber tubes. In existing technologies, rotor mounts usually employ an open clamping structure to connect to the carbon fiber tubes, using either separate or integrated clamping blocks to compress them. This results in localized shearing of the carbon fiber tubes, a small stress area, and even excessive screw preload, easily causing the carbon fiber tubes to burst. Increasing the thickness of the carbon fiber tubes to prevent bursting would compromise the drone's lightweight requirements. Summary of the Invention

[0003] Therefore, it is necessary to provide a power system for a multi-rotor unmanned aerial vehicle (UAV), and the specific technical solution is as follows.

[0004] A power system for a multi-rotor unmanned aerial vehicle (UAV) includes:

[0005] The tube clamp includes an outer shell and a carbon tube mounting base installed inside the outer shell; the carbon tube mounting base is provided with a hollow mounting through hole;

[0006] The carbon tube inner support includes an inner support tube body and a horizontal positioning boss; the horizontal positioning boss is connected to the outside of the inner support tube body; the horizontal positioning boss is connected to the carbon tube mounting base, so that an assembly gap is formed between the inner support tube body and the mounting through hole.

[0007] The carbon tube has a horizontal positioning groove at its end; the carbon tube is inserted into the assembly gap, and the horizontal positioning groove engages with the horizontal positioning boss; after the carbon tube mounting base, the carbon tube inner support, and the carbon tube are connected, the carbon tube mounting base and the carbon tube inner support clamp the carbon tube.

[0008] The motor is connected to the side of the pipe clamp.

[0009] Furthermore, the carbon tube mounting base is provided with a first through hole, the carbon tube is provided with a second through hole, and the carbon tube inner support is provided with a first threaded hole; a first screw passes through the first through hole and the second through hole in sequence and then connects with the first threaded hole to clamp the carbon tube mounting base and the carbon tube inner support.

[0010] Furthermore, the carbon tube mounting base is provided with a third through hole, and the horizontal positioning boss is provided with a second threaded hole; the second screw passes through the third through hole and connects with the second threaded hole to connect the horizontal positioning boss with the carbon tube mounting base.

[0011] Furthermore, the carbon tube inner support is a tubular structure, and the carbon tube inner support is provided with symmetrically arranged first stress relief grooves; the first stress relief grooves extend from the end of the carbon tube inner support towards the middle position, and the first stress relief grooves penetrate the tube wall of the carbon tube inner support.

[0012] Furthermore, multiple first clamping springs are provided between the outer shell and the carbon tube mounting base; a clamping groove is formed between adjacent first clamping springs, the clamping groove including an open end and an arc-shaped positioning surface opposite to the open end, the open end penetrating one side wall of the outer shell; the first clamping springs are provided with mounting holes, and the mounting holes on each first clamping spring are arranged coaxially; multiple second clamping springs are provided on the motor, the second clamping springs are provided with arc-shaped grooves, and the arc-shaped grooves are arranged coaxially with the arc-shaped positioning surface; the second clamping springs are inserted into the clamping grooves; an adjusting screw passes through the mounting hole and the arc-shaped groove and connects to the first clamping spring, so that the first clamping spring clamps the second clamping spring.

[0013] Furthermore, the mounting hole on the last of the multiple first clamping springs arranged along the axial direction of the mounting hole is a third threaded hole, while the mounting holes on the remaining first clamping springs are through holes; the end of the third threaded hole near the through hole has a partially smooth surface.

[0014] Furthermore, the first clamping spring is provided with two oppositely arranged angle adjustment slots, which are exposed outside the outer shell; the angle adjustment slots include a first reference surface, and the first reference surfaces of the two angle adjustment slots are coplanar and pass through the center of the arc-shaped positioning surface.

[0015] Furthermore, the angle adjustment range of the motor is between -10° and +10°.

[0016] Furthermore, the outer casing has an ESC compartment on its side wall, and an ESC is installed recessed inside the ESC compartment; a receiving space is formed between the carbon tube mounting base and the ESC, and the receiving space is connected to the ESC compartment; the outer casing also has a lead wire inlet, which is connected to the receiving space, so that the motor cable enters the ESC compartment from the lead wire inlet through the receiving space.

[0017] Furthermore, the outer casing is connected to a front cover and a rear cover at both ends, thereby sealing the inside of the tube clamp seat.

[0018] Beneficial effects: 1. The power system of a multi-rotor UAV provided by the present invention uses a carbon tube mounting base and a carbon tube inner support to clamp and fix the carbon tube, forming a through-type inner and outer clamping structure. The carbon tube has a large force-bearing area and uniform force, which ensures strong axial and radial constraints while basically eliminating the possibility of the carbon tube being crushed.

[0019] 2. The power system of the multi-rotor UAV provided by the present invention can adjust the tilt angle of the rotor, adapt to different flight conditions and flight scenarios, and the tilt angle adjustment method is simple and flexible to use.

[0020] 3. The power system of the multi-rotor UAV provided by the present invention has a compact overall structure, the ESC adopts a recessed installation, which has stronger anti-vibration and anti-impact capabilities, and the lead wires are internally routed for high reliability. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the overall structure of the power system;

[0023] Figure 2 This is a schematic diagram of an explosion of the power system;

[0024] Figure 3 A schematic diagram of the internal support structure of carbon nanotubes;

[0025] Figure 4 This is a schematic diagram of the structure of carbon nanotubes;

[0026] Figure 5 This is a cross-sectional view of the carbon nanotubes after installation.

[0027] Figure 6 This is a schematic diagram of the top surface of the pipe clamp seat;

[0028] Figure 7 For along Figure 6 A cross-sectional schematic diagram of AA in the middle;

[0029] Figure 8 This is a schematic diagram of the end face of the pipe clamp seat;

[0030] Figure 9 For along Figure 8 Cross-sectional schematic diagram of BB;

[0031] Figure 10 This is a schematic diagram of the motor;

[0032] Figure 11 This is a cross-sectional view of the motor mounted on the pipe clamp.

[0033] Figure 12 This is a schematic diagram of motor angle adjustment;

[0034] Figure 13 for Figure 10 Enlarged view of region A in the middle;

[0035] Figure 14 Another view of the motor;

[0036] Figure 15 This is a schematic diagram of the pipe clamp seat structure;

[0037] Figure 16 An exploded view of the motor and pipe clamp assembly;

[0038] Figure 17 This is an exploded view of the carbon nanotube assembly process.

[0039] Explanation of reference numerals in the attached diagram: 1. Tube clamp seat; 2. Carbon tube inner support; 3. Carbon tube; 4. Motor; 5. First screw; 6. Second screw; 7. Adjusting screw; 8. Electric speed controller; 9. Front cover; 10. Rear cover;

[0040] 11. Outer casing; 12. Carbon nanotube mounting base; 13. Mounting via; 14. First via; 15. Clearance hole; 16. Third via; 17. Electrical control chamber;

[0041] 101. First clamping spring; 102. Clamping groove; 103. Arc-shaped positioning surface; 104. Mounting hole; 105. Third threaded hole; 106. Smooth surface;

[0042] 21. Inner support tube body; 22. Horizontal positioning boss; 23. Assembly reference step; 24. First threaded hole; 25. Second threaded hole; 26. First stress relief groove;

[0043] 31. Horizontal positioning groove; 32. Second through hole;

[0044] 401. Second clamping spring; 402. Arc groove; 403. Second stress relief groove; 404. Angle adjustment groove; 405. First reference surface. Detailed Implementation

[0045] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0046] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0047] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0048] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0049] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0050] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0051] Example

[0052] Reference Figure 1 and Figure 2 As shown, this embodiment provides a power system for a multi-rotor unmanned aerial vehicle (UAV), including a tube clamp 1, a carbon tube inner support 2, a carbon tube 3, and a motor 4. (Refer to...) Figure 15 As shown, the tube clamp seat 1 includes an outer shell 11 and a carbon tube mounting seat 12 installed inside the outer shell 11. The carbon tube mounting seat 12 has a hollow mounting through hole 13, and the inner diameter of the mounting through hole 13 forms a micro-gap with the outer diameter of the carbon tube 3, which facilitates the assembly of the carbon tube 3 into the carbon tube mounting seat 12. The motor 4 is installed on the side of the tube clamp seat 1, and the motor 4 is used to connect with the rotor and drive the rotor to rotate.

[0053] Reference Figure 3 As shown, the carbon tube inner support 2 includes an inner support tube body 21 and a horizontal positioning boss 22. The horizontal positioning boss 22 is connected to the outside of the inner support tube body 21. The horizontal positioning boss 22 abuts against the inner wall of the mounting hole 13, so that the horizontal positioning boss 22 is connected to the carbon tube mounting seat 12, thereby forming an assembly gap between the inner support tube body 21 and the mounting hole 13. The thickness of the assembly gap is not less than the thickness of the carbon tube 3, so that the carbon tube 3 can be inserted into the assembly gap.

[0054] Reference Figure 4As shown, the end of the carbon tube 3 is provided with a horizontal positioning groove 31. The carbon tube 3 is inserted into the assembly gap, and the horizontal positioning groove 31 engages with the horizontal positioning boss 22. The horizontal positioning boss 22 can, on the one hand, form an assembly gap between the carbon tube 3 mounting base and the carbon tube inner support 2, and on the other hand, it can position the carbon tube 3 during assembly to prevent the carbon tube 3 from rotating. After the carbon tube mounting base 12, the carbon tube inner support 2, and the carbon tube 3 are connected, the carbon tube mounting base 12 and the carbon tube inner support 2 clamp the carbon tube 3. A micro-gap fit is also formed between the inner diameter of the carbon tube 3 and the outer diameter of the carbon tube inner support 2, which facilitates the insertion of the carbon tube 3 into the assembly gap. After the carbon tube 3 is inserted into the assembly gap, the first screw 5 connects the carbon tube mounting base 12, the carbon tube inner support 2, and the carbon tube 3, so that the carbon tube mounting base 12 and the carbon tube inner support 2 clamp the carbon tube 3, so that the carbon tube mounting base 12 and the carbon tube inner support 2 form local friction between the inner and outer diameters of the carbon tube 3, respectively, to resist torque; thus, the stress distribution inside and outside the carbon tube 3 is uniform, and the first screw 5 passes through the carbon tube mounting base 12, the carbon tube 3, and the carbon tube inner support 2, which has a strong axial and radial constraint on the entire structure.

[0055] The power system of the multi-rotor UAV provided in this embodiment uses carbon tube mounting seat 12 and carbon tube inner support 2 to clamp and fix carbon tube 3, forming a through-type inner and outer clamping structure. The carbon tube 3 has a large force-bearing area and uniform force, which ensures strong axial and radial constraints while basically eliminating the possibility of the carbon tube 3 being crushed.

[0056] Specifically, in this embodiment, the end of the carbon tube inner support 2 is further provided with an assembly reference step 23. This assembly reference step 23 is arranged along the contour of the end of the carbon tube inner support 2 and is arc-shaped. When the carbon tube 3 is assembled into the assembly gap, the end of the carbon tube 3 is positioned by the assembly reference step 23 abutting against it. In other embodiments, the assembly reference step 23 may not be provided; positioning may be achieved solely by the horizontal positioning boss 22, or other positioning references may be provided.

[0057] Specifically, refer to Figure 5 As shown, the carbon tube mounting base 12 has a first through hole 14 that penetrates the carbon tube mounting base 12, and the outer shell 11 has a clearance hole 15 corresponding to the first through hole 14 to facilitate the installation of the first screw 5. The carbon tube 3 has a second through hole 32, and the carbon tube inner support 2 has a first threaded hole 24, so that the first through hole 14, the second through hole 32, and the first threaded hole 24 are arranged coaxially. The first screw 5 passes through the first through hole 14 and the second through hole 32 in sequence and then connects to the first threaded hole 24. By applying a certain preload to the first screw 5, the carbon tube inner support 2 and the carbon tube mounting base 12 clamp the carbon tube 3, which is converted into frictional force between the carbon tube 3 and the carbon tube inner support 2 and the carbon tube mounting base 12.

[0058] In this embodiment, the inner support 2 of the carbon tube is provided with two sets of first threaded holes 24, each set containing four first threaded holes 24, that is, the inner support 2 of the carbon tube is provided with eight first threaded holes 24. Within the same set, adjacent threaded holes are arranged at 90° intervals. Correspondingly, the carbon tube 3 is provided with second through holes 32 corresponding to each of the first threaded holes 24, and the carbon tube mounting base 12 is provided with first through holes 14 corresponding to each of the first threaded holes 24. By setting eight constraint points, even if several screws loosen or fail, it will not affect the power system's ability to maintain a normal attitude during landing, avoiding crashes caused by fastening problems, and exhibiting extremely high reliability.

[0059] Specifically, the carbon tube mounting base 12 is provided with a third through hole 16, and the horizontal positioning boss 22 is provided with a second threaded hole 25. The third through hole 16 penetrates the carbon tube mounting base 12, and the second screw 6 passes through the third through hole 16 and connects to the second threaded hole 25, thereby connecting the horizontal positioning boss 22 to the tube clamp seat 1. Specifically, there are two horizontal positioning bosses 22, which are symmetrically arranged along the axis of the carbon tube inner support 2, such that the interval between the second threaded hole 25 and the first threaded hole 24 is 45°. The carbon tube inner support 2 is a tubular structure, and the carbon tube inner support 2 is provided with symmetrically arranged first stress relief grooves 26; the first stress relief grooves 26 extend from the end of the carbon tube inner support 2 towards the middle position, and the first stress relief grooves 26 penetrate the tube wall of the carbon tube inner support 2. Two sets of first stress relief grooves 26 are arranged, each set including two first stress relief grooves 26 symmetrically arranged along the axis of the carbon tube inner support 2. The two sets of first stress relief grooves 26 are symmetrically arranged along the central radial plane of the carbon tube inner support 2. By setting the first stress relief grooves 26 on the carbon tube inner support 2, the stress level is reduced when the first screw 5 locks the carbon tube mounting seat 12, the carbon tube 3, and the carbon tube inner support 2.

[0060] When a drone faces different flight scenarios, appropriately adjusting the rotor tilt angle can improve its flight stability and controllability. The power system of a multi-rotor drone provided in this embodiment can adjust the rotor tilt angle within the range of -10° to +10° to meet the requirements of different flight zones and scenarios.

[0061] Specifically, refer to Figures 6 to 9As shown, a plurality of first clamping springs 101 are provided between the outer shell 11 and the carbon nanotube mounting base 12, forming a clamping groove 102 between adjacent first clamping springs 101. The clamping groove 102 includes an open end and an arc-shaped positioning surface 103 opposite to the open end, the arc-shaped positioning surface 103 being located on the outer surface of the carbon nanotube mounting base 12. The open end penetrates one side wall of the outer shell 11; each first clamping spring 101 has mounting holes 104, with the mounting holes 104 on each first clamping spring 101 arranged coaxially, and each first clamping spring 101 having two mounting holes 104. (Refer to...) Figure 10 As shown, the motor 4 is equipped with multiple second clamping springs 401, the number of which is the same as the number of clamping slots 102. Each second clamping spring 401 has an arc-shaped groove 402, which is coaxially arranged with the arc-shaped positioning surface 103. Each second clamping spring 401 is inserted into a corresponding clamping slot 102 and abuts against the arc-shaped positioning surface 103. (Refer to...) Figure 11 As shown, the adjusting screw 7 passes through the arc groove 402 and connects to the first clamping spring 101, so that the first clamping spring 101 clamps the second clamping spring 401.

[0062] The power system of the multi-rotor UAV provided in this embodiment is a coaxial multi-rotor UAV power system. Motors 4 and corresponding rotors are respectively installed on the upper and lower sides of the tube clamp 1. The angle adjustment diagram is shown below. Figure 12 As shown in the diagram. Although the rotor is not shown, it can be understood that the rotor is mounted on motor 4, and the tilt angle of the rotor can be adjusted by adjusting the angle of motor 4.

[0063] Specifically, continue to refer to Figure 9 As shown, the last of the multiple first clamping springs 101 arranged along the axial direction of the mounting hole 104 has a third threaded hole 105 on its mounting hole 104, while the mounting holes 104 on the remaining first clamping springs 101 are through holes; the third threaded hole 105 has a partially smooth surface 106 at the end near the through hole. After applying a certain preload to the adjusting screw 7, the first clamping spring 101 clamps the second clamping spring 401, converting it into friction between the first clamping spring 101 and the second clamping spring 401, thereby fixing the angle of the motor 4 and thus fixing the tilt angle of the rotor. When it is necessary to adjust the tilt angle of the rotor, it is only necessary to loosen the adjusting screw 7 to adjust the angle of the motor 4 along the contour of the arc-shaped positioning surface 103. This adjustment process does not require unloading the rotor or adding an additional angle adjustment block; the adjustment process is simple, convenient, and efficient. By providing a partially smooth surface 106 at the end of the third threaded hole 105 near the through hole, shear components are resisted, protecting the threads.

[0064] Specifically, refer to Figure 13As shown, in this embodiment, the root of the second clamping spring 401 is also provided with a second stress relief groove 403, which is used to improve the stress concentration at the root when the second clamping spring 401 is clamped with the first clamping spring 101.

[0065] Specifically, refer to Figure 14 As shown, the first clamping spring 101 is provided with two opposing angle adjustment slots 404, which protrude from the exterior of the outer casing 11. Each angle adjustment slot 404 includes a first reference surface 405, and the first reference surfaces 405 of the two angle adjustment slots 404 are coplanar and pass through the center of the arc-shaped positioning surface 103. Using the first reference surface 405 as a zero-line reference, it facilitates quick angle adjustment or leveling by the operator in conjunction with equipment such as an electronic level.

[0066] Specifically, refer to Figure 15 As shown, the outer casing 11 has electrical control chambers 17 on its opposite side walls, and an electrical control unit 8 is recessed into each chamber 17. A receiving space is formed between the carbon tube mounting base 12 and the electrical control unit 8, and this receiving space is connected to the electrical control chamber 17. The outer casing 11 also has a lead wire inlet, which is connected to the receiving space, allowing the cable of the motor 4 to enter the electrical control chamber 17 from the lead wire inlet through the receiving space. This ensures that the cable between the motor 4 and the electrical control unit 8 is routed inside the tube clamp 1, improving reliability.

[0067] Specifically, the outer shell 11 is connected to a front cover 9 and a rear cover 10 at both ends, which seals the inside of the pipe clamp seat 1 and provides protection for the internal structure of the pipe clamp seat 1.

[0068] The assembly process of the power system of a multi-rotor UAV provided in this embodiment includes: assembling the motor 4 and the tube clamp seat 1, assembling the carbon tube 3, and assembling the electronic speed controller 8.

[0069] When assembling the motor 4 and the tube clamp seat 1, insert the second clamping piece into the clamping groove 102 and make the second clamping piece cooperate with the arc-shaped positioning surface 103. Then install the adjusting screw 7, so that the adjusting screw 7 passes through the mounting hole 104 and the arc-shaped groove 402 and connects to the third threaded hole 105. By applying a pre-tightening force to the screw, it is converted into the frictional force between the first clamping spring 101 and the second clamping spring 401, thereby fixing the angle of the motor 4 and fixing the angle of the rotor.

[0070] When assembling the carbon tube 3, firstly, the second screw 6 is used to assemble the inner support 2 of the carbon tube into the assembly through hole, so that an assembly gap is formed between the inner support tube body 21 and the assembly through hole. Then, the carbon tube 3 is inserted into the assembly gap and positioned by engaging the horizontal positioning groove 31 with the horizontal positioning boss 22. Then, the first screw 5 passes through the carbon tube mounting base 12 and the carbon tube 3 and connects to the first threaded hole 24 on the inner support 2 of the carbon tube. A certain preload is applied to the first screw 5, which is converted into the frictional force between the inner support 2 of the carbon tube and the carbon tube mounting base 12 on the carbon tube 3.

[0071] It should be noted that the order of assembling the motor 4 and the tube clamp seat 1, as well as the order of assembling the carbon tube 3, can be interchanged. One end of the third through hole 16 is located inside the electronic control chamber 17, so the electronic control 8 should be installed after the carbon tube 3 is installed, and finally the front cover 9 and the rear cover 10 should be installed.

[0072] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0073] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A power system for a multi-rotor unmanned aerial vehicle, characterized in that, include: The tube clamp includes an outer shell and a carbon tube mounting base installed inside the outer shell; the carbon tube mounting base is provided with a hollow mounting through hole; The carbon tube inner support includes an inner support tube body and a horizontal positioning boss; the horizontal positioning boss is connected to the outside of the inner support tube body; the horizontal positioning boss is connected to the carbon tube mounting base, so that an assembly gap is formed between the inner support tube body and the mounting through hole. The carbon tube has a horizontal positioning groove at its end; the carbon tube is inserted into the assembly gap, and the horizontal positioning groove engages with the horizontal positioning boss; after the carbon tube mounting base, the carbon tube inner support, and the carbon tube are connected, the carbon tube mounting base and the carbon tube inner support clamp the carbon tube. The motor is connected to the side of the pipe clamp. Multiple first clamping springs are provided between the outer shell and the carbon tube mounting base; a clamping groove is formed between adjacent first clamping springs, the clamping groove including an open end and an arc-shaped positioning surface opposite to the open end, the open end penetrating one side wall of the outer shell; the first clamping springs are provided with mounting holes, and the mounting holes on each first clamping spring are arranged coaxially; the motor is provided with multiple second clamping springs, the second clamping springs are provided with arc-shaped grooves, and the arc-shaped grooves are arranged coaxially with the arc-shaped positioning surface; the second clamping springs are inserted into the clamping grooves; an adjusting screw passes through the mounting hole and the arc-shaped groove and connects to the first clamping spring, so that the first clamping spring clamps the second clamping spring; The first clamping spring is provided with two oppositely arranged angle adjustment slots, which are exposed outside the outer shell; the angle adjustment slots include a first reference surface, and the first reference surfaces of the two angle adjustment slots are coplanar and pass through the center of the arc-shaped positioning surface.

2. The power system for a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that, The carbon tube mounting base is provided with a first through hole, the carbon tube is provided with a second through hole, and the carbon tube inner support is provided with a first threaded hole; a first screw passes through the first through hole and the second through hole in sequence and then connects to the first threaded hole, thereby clamping the carbon tube mounting base and the carbon tube inner support together.

3. The power system for a multi-rotor unmanned aerial vehicle according to claim 2, characterized in that, The carbon nanotube mounting base is provided with a third through hole, and the horizontal positioning boss is provided with a second threaded hole; the second screw passes through the third through hole and connects with the second threaded hole to connect the horizontal positioning boss with the carbon nanotube mounting base.

4. The power system of a multi-rotor unmanned aerial vehicle according to claim 2, characterized in that, The carbon tube inner support is a tubular structure, and the carbon tube inner support is provided with symmetrically arranged first stress relief grooves. The first stress relief groove extends from the end of the carbon tube inner support towards the middle position, and the first stress relief groove penetrates the tube wall of the carbon tube inner support.

5. The power system of a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that, The last of the multiple first clamping springs arranged along the axial direction of the mounting hole has a third threaded hole, while the mounting holes on the remaining first clamping springs are through holes; the end of the third threaded hole near the through hole has a partially smooth surface.

6. The power system of a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that, The angle adjustment range of the motor is between -10° and +10°.

7. The power system of a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that, The outer casing has an ESC compartment on its side wall, and an ESC is installed recessedly inside the ESC compartment; a receiving space is formed between the carbon tube mounting base and the ESC, and the receiving space is connected to the ESC compartment; the outer casing also has a lead wire inlet, which is connected to the receiving space, so that the motor cable enters the ESC compartment from the lead wire inlet through the receiving space.

8. A power system for a multi-rotor unmanned aerial vehicle according to any one of claims 1 to 7, characterized in that, The outer casing is connected to a front cover and a rear cover at both ends, which seals the inside of the tube clamp seat.

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