An unmanned aerial vehicle motor

Abstract

This invention discloses a drone motor, relating to the field of drone motor technology. The invention includes a housing, with a stator core connected to the inner ring of the housing. Four heat dissipation holes are formed at both ends of the stator core, and each of the four heat dissipation holes has an integrally formed positioning boss at its lower interior. Through the arrangement of the stator core, heat dissipation holes, first heat dissipation fins, and second heat dissipation fins, the fan-shaped heat dissipation holes in the stator core can accommodate multiple sets of first heat dissipation fins, directly conducting the iron loss heat generated by the core's operation. The bottom ring, second heat dissipation fins, and top ring, closely attached to the stator windings, can quickly dissipate the copper loss heat generated by the windings being energized, increasing the heat dissipation area, improving the overall natural heat dissipation efficiency, alleviating heat accumulation inside the motor, reducing the possibility of high-temperature melting and short circuits in the enameled wire and irreversible demagnetization of the rotor magnets, reducing the probability of the flight control overheat protection program limiting the motor's output torque, and improving the load capacity, wind resistance, and continuous flight performance of heavy-duty drones.

Description

Technical Field

[0001] This invention relates to the field of drone motor technology, specifically to a drone motor. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aerial vehicles that do not require human operation. They rely on flight control systems, power units, and navigation modules to perform autonomous takeoff and landing, hovering, and routed flight. They can be broadly categorized into consumer-grade and heavy-duty industrial UAVs. Heavy-duty industrial UAVs, with their large payload capacity, are widely used in agricultural and forestry plant protection, mountain material transportation, power line inspection, and emergency rescue. They can hover for extended periods and perform continuous high-load operations, placing stringent requirements on the continuous output capacity, heat dissipation stability, and mechanical reliability of the power system. Multi-rotor heavy-duty UAVs use brushless motors as their core power source, relying on the motors to drive the propellers and generate lift. The motor's operating state directly determines the overall payload, wind resistance, and continuous operation performance of the aircraft.

[0003] External rotor brushless DC motors are the mainstream drive components for drones. Unlike internal rotor motors with the rotor built-in, their structure features a centrally fixed stator and permanent magnets embedded in the inner wall of the outer rotor. During operation, the outer rotor rotates around the inner stator as a whole. This motor uses an electronic commutation structure instead of traditional carbon brush commutation, resulting in lower operating losses and fewer maintenance requirements. Furthermore, its mass is distributed on the periphery, resulting in greater rotational inertia, smoother operation at low speeds and higher torque output density, making it suitable for the continuous high-torque output requirements of heavy-duty drones.

[0004] The core heat source of the entire aircraft is concentrated in the internal stator structure: copper loss is generated when the stator winding is energized, and iron loss is generated when the stator core is alternately magnetized. All the heat is accumulated in the small space inside the motor, and the heat dissipation structure design directly limits the upper limit of the motor's long-term heavy-load operation. Existing external rotor motors for heavy-load UAVs generally have multiple shortcomings in heat dissipation structure, mechanical limit, and bearing support, making it difficult to adapt to long-term high-load continuous operation conditions. Firstly, conventional motors lack a layered composite forced air cooling structure. The stator core and stator windings rely solely on passive heat dissipation from the outer shell, and the heat generated by the two types of heat sources is prone to continuous accumulation. The heat dissipation space layout is simple, and the heat dissipation efficiency is low. After the temperature rises rapidly and exceeds the limit, it will increase the probability of high-temperature melting and short circuit of the enameled wire and irreversible demagnetization of the rotor magnets. At the same time, the flight control overheat protection program will limit the motor's output thrust, reducing the aircraft's load capacity, wind resistance, and continuous flight capability. Summary of the Invention

[0005] Therefore, the purpose of this invention is to provide a drone motor to solve the technical problems mentioned in the background section.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a drone motor, comprising a housing, an inner ring of which is connected to a stator core, four heat dissipation holes at both ends of the stator core, a positioning boss integrally formed below each of the four heat dissipation holes, and four sets of first heat dissipation fins respectively connected inside the four heat dissipation holes; each of the four sets of first heat dissipation fins has a buckle and a buckle plate integrally formed at both ends, and outer and inner bent fins integrally formed on both sides of each of the four sets of first heat dissipation fins; a stator core is wound around the stator slot of the stator core. The stator winding has a bottom ring connected to its top end. The bottom ring has multiple second heat dissipation fins integrally formed on its top, and a top ring is welded to the top of each of the multiple second heat dissipation fins. The stator core has a stator base integrally formed at its bottom end. Both the stator base and the inner ring of the stator core are connected to support bearings. A central shaft passes through the top of each of the two support bearings. A centrifugal impeller is connected to the outside of the central shaft via a bracket. Centrifugal blades are integrally formed inside the centrifugal impeller. An air duct is provided between the centrifugal impeller and the centrifugal blades. A clearance groove is provided at the bottom of the centrifugal blades.

[0007] By adopting the above technical solution, the heat dissipation holes opened on the stator core can be equipped with multiple sets of first heat dissipation fins to dissipate the iron heat loss of the core. The bottom ring, the second heat dissipation fins and the top ring work together to dissipate the copper heat loss of the stator winding. The centrifugal impeller and the centrifugal blades work together to form a circulating airflow to simultaneously force-cool the two heat sources. The support bearing provides stable support for the central shaft. The positioning boss, the buckle and the buckle plate work together to constrain the first heat dissipation fins. The clearance groove reduces the collision between the rotating parts and the heat dissipation structure. The overall structure works together to improve the heat dissipation performance of the motor and the stability of mechanical operation.

[0008] Furthermore, the thickness of the first and second heat dissipation fins is 0.2 mm to 0.5 mm.

[0009] By adopting the above technical solutions, thin heat dissipation fins can improve their own heat conduction rate, while increasing the number of fins in a unit space, expanding the overall heat exchange area, and further improving the efficiency of heat conduction and dissipation inside the motor.

[0010] Furthermore, both the outer and inner bent fins have a concave bottom side, and the positioning boss abuts against the concave bottom side of the outer and inner bent fins.

[0011] By adopting the above technical solution, the positioning boss and the concave bottom of the bent fin mutually limit each other, which can form an axial constraint on the first heat dissipation fin, reducing the possibility of axial detachment of the fin under motor operation vibration conditions.

[0012] Furthermore, the width of the outer ring bent fins is greater than the width of the inner ring bent fins, the cross-section of the heat dissipation hole is fan-shaped, and the outer ring bent fins and the inner ring bent fins are tightly fitted to the inner wall of the heat dissipation hole.

[0013] By adopting the above technical solution, bent fins of varying widths are stacked to form a fan-shaped whole, which fits the inner wall of the fan-shaped heat dissipation hole, increases the thermal contact area between the fins and the stator core, and shortens the path of heat transfer from the core to the cooling airflow.

[0014] Furthermore, the space between the bottom ring and the stator winding is filled with high thermal conductivity silicone grease, and a plurality of second heat dissipation fins are distributed in a ring array, with the second heat dissipation fins fitting into the clearance groove.

[0015] By adopting the above technical solutions, high thermal conductivity silicone grease can eliminate the thermal gap between the winding and the second heat dissipation fins, the ring array arrangement expands the heat dissipation coverage of the winding, and the clearance groove can reserve space for the centrifugal blades to move, reducing the probability of component wear.

[0016] Furthermore, the two support bearings are angular contact bearings, and the two support bearings are arranged face-to-face.

[0017] By adopting the above technical solution, the face-to-face arranged double angular contact bearings can simultaneously bear axial loads and radial loads, reduce the axial movement and radial wobble of the central shaft under flight conditions, and reduce the frictional loss between the central shaft and the stator core.

[0018] Furthermore, the inner ring of the central shaft is threaded, and the centrifugal impeller is detachably connected to the central shaft by bolts.

[0019] By adopting the above technical solution, the detachable clamping assembly method of threads and bolts facilitates the disassembly, assembly, and maintenance of the centrifugal impeller, while ensuring the tightness of the connection between the centrifugal impeller and the central shaft, and maintaining stable airflow output.

[0020] Furthermore, the centrifugal blades are provided with twelve to eighteen blades, and the outer ring of the centrifugal impeller is interference-fitted with the inner ring of the motor rotor.

[0021] By adopting the above technical solution, the synchronous rotation of multiple centrifugal blades can increase the airflow circulation. The impeller and rotor rotate synchronously without relative displacement, reducing airflow turbulence and making the airflow through the heat dissipation fins more stable and uniform.

[0022] Furthermore, each group of the first heat dissipation fins consists of forty to sixty first heat dissipation fins stacked together, with four groups totaling one hundred and sixty to two hundred and fourteen first heat dissipation fins, for motors ranging from 2kW to 5kW.

[0023] By adopting the above technical solution, the heat generation requirements of small and medium power heavy-duty motors can be adapted. The reasonable number of stacked fins can control the motor volume while matching the heat dissipation load under the corresponding power conditions.

[0024] Furthermore, each group of first heat dissipation fins consists of seventy to one hundred first heat dissipation fins stacked together, with four groups totaling two hundred and eighty to four hundred first heat dissipation fins, for motors ranging from 6kW to 15kW.

[0025] By adopting the above technical solutions, a larger number of stacked fins can significantly increase the total heat exchange area, adapting to the greater heat generated by high-power, heavy-duty motors operating under high loads for extended periods, and meeting the heat dissipation requirements under high-temperature conditions.

[0026] In summary, the present invention has the following main beneficial effects:

[0027] 1. This invention, through the arrangement of stator core, heat dissipation holes, first heat dissipation fins and second heat dissipation fins, allows the fan-shaped heat dissipation holes in the stator core to accommodate multiple sets of first heat dissipation fins, directly conducting the iron loss heat generated by the core's operation. The bottom ring, second heat dissipation fins and top ring arranged close to the stator winding can quickly conduct the copper loss heat generated by the winding's energization, increasing the heat dissipation area, improving the overall natural heat dissipation efficiency, alleviating heat accumulation inside the motor, reducing the possibility of high-temperature melting and short circuit of enameled wire and irreversible demagnetization of rotor magnets, reducing the probability of flight control overheat protection programs limiting motor output pull, and improving the load, wind resistance and continuous flight performance of heavy-duty UAVs;

[0028] 2. This invention, through the setting of outer ring bent fins, inner ring bent fins, buckles, buckle plates and positioning bosses, integrates bent fins of different widths on both sides of a single first heat dissipation fin. After stacking, the whole assembly fits the fan-shaped inner wall of the heat dissipation hole, increasing the heat conduction contact area. The buckles and buckle plates at the upper and lower ends of the fins can realize the interlayer buckling and limiting of multiple fins. The buckling area is laser welded, and the first heat dissipation fin is assembled with the heat dissipation hole through interference fit. Combined with the structure of the positioning boss and the concave bottom of the bent fin, the entire first heat dissipation fin is constrained in both axial and radial directions, reducing the phenomenon of heat dissipation fin separation, axial detachment and radial movement under motor vibration conditions, and ensuring stable heat exchange capacity under long-term operation.

[0029] 3. The present invention, through the arrangement of support bearings, central shaft, bracket, centrifugal impeller, centrifugal blades, air duct, and clearance groove, allows two sets of angular contact support bearings arranged face-to-face to reduce the axial and radial movement of the central shaft under flight conditions, thereby reducing frictional losses between the central shaft and the stator core. The centrifugal impeller rotates synchronously with the rotor to generate a continuous external circulating airflow, which blows on the first and second heat dissipation fins, providing forced air cooling for the two types of heat sources: the stator core and the stator winding. The clearance groove at the bottom of the blades provides clearance for the second heat dissipation fins, top ring, and bottom ring, reducing the probability of collision and wear between rotating parts and the stator heat dissipation structure, and extending the overall service life of the motor. Attached Figure Description

[0030] Figure 1This is a schematic diagram of the overall structure of the present invention;

[0031] Figure 2 This is a cross-sectional structural diagram of the present invention;

[0032] Figure 3 This is a schematic diagram of the exploded shell structure of the present invention;

[0033] Figure 4 This is a schematic diagram of the exploded structure of the centrifugal impeller of the present invention;

[0034] Figure 5 This is a schematic diagram of the exploded structure of the stator core of the present invention;

[0035] Figure 6 This is a schematic diagram of one set of first heat dissipation fin stacking structures of the present invention;

[0036] Figure 7 For the present invention Figure 6 Enlarged view of the structure at point A in the image;

[0037] Figure 8 This is a bottom view of the first heat dissipation fin structure of the present invention.

[0038] In the diagram: 1. Outer shell; 2. Stator core; 3. Stator winding; 4. Support bearing; 5. Stator base; 6. First heat dissipation fin; 7. Outer ring bent fin; 8. Inner ring bent fin; 9. Buckle; 10. Buckle plate; 11. Bottom ring; 12. Second heat dissipation fin; 13. Top ring; 14. Central shaft; 15. Bracket; 16. Centrifugal impeller; 17. Centrifugal blade; 18. Air duct; 19. Clearance groove; 20. Heat dissipation hole; 21. Positioning boss. Detailed Implementation

[0039] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0040] The embodiments of the present invention will now be described.

[0041] Example 1:

[0042] A type of drone motor, such as Figures 2-8As shown, the device includes an outer shell 1, with a stator core 2 connected to its inner ring. The stator core 2 has four heat dissipation holes 20 at both ends, each with a fan-shaped cross-section to accommodate heat dissipation fins and form an axial airflow channel. Four sets of first heat dissipation fins 6 are connected inside each of the four heat dissipation holes 20, responsible for dissipating the heat generated by the stator core 2 during operation. Each of the four sets of first heat dissipation fins 6 has a snap-fit ​​9 and a snap-fit ​​plate 10 integrally formed at both ends, enabling interlayer locking and limiting of multiple first heat dissipation fins 6. Each of the four sets of first heat dissipation fins 6 has an outer ring bent fin 7 and an inner ring bent fin 8 integrally formed on both sides. The width of the outer ring bent fin 7 is greater than the width of the inner ring bent fin 8, stacking them to fit the contour of the fan-shaped heat dissipation holes 20 and increase the heat conduction area. The outer ring bent fin 7 and the inner ring bent fin 8 are tightly fitted to the inner wall of the heat dissipation holes 20, achieving interference fit and reducing the risk of detachment. Secondly, the tight fit reduces air gaps and improves heat dissipation efficiency. Each of the four heat dissipation holes 20 has an integrally formed positioning boss 21 at its lower interior. The bottom side of both the outer and inner bent fins 7 and 8 has a recessed area. The positioning boss 21 abuts against the recessed area on the bottom side of the outer and inner bent fins 7 and 8, forming an axial limiting constraint on the first heat dissipation fin 6. The stator core 2 has a stator winding 3 wrapped around its stator slot. A bottom ring 11 is connected to the top of the stator winding 3. High thermal conductivity silicone grease is filled between the bottom ring 11 and the stator winding 3. Multiple second heat dissipation fins 12 are integrally formed on the top of the bottom ring 11, arranged in a ring array. The thickness of the first heat dissipation fin 6 and the second heat dissipation fins 12 is 0.2mm to 0.5mm. A top ring 13 is welded to the top of each of the multiple second heat dissipation fins 12, forming a complete winding heat dissipation assembly.

[0043] See Figures 1-6 In the above embodiment, a stator base 5 is integrally formed at the bottom end of the stator core 2; both the stator base 5 and the inner ring of the stator core 2 are connected to support bearings 4. The two support bearings 4 are angular contact bearings and are arranged face to face to simultaneously bear axial and radial loads and reduce the movement of the central shaft 14; the top of the two support bearings 4 is provided with the central shaft 14, the inner ring of the central shaft 14 is threaded, and the centrifugal impeller 16 is connected to the outside of the central shaft 14 through the bracket 15. The centrifugal impeller 16 is detachably connected to the central shaft 14 by bolts, which facilitates the disassembly and maintenance of the centrifugal impeller 16 while ensuring a stable connection; the centrifugal blades 17 are integrally formed inside the centrifugal impeller 16, and an air duct 18 is provided between the centrifugal impeller 16 and the centrifugal blades 17 to form airflow for forced air cooling; the bottom of the centrifugal blades 17 is provided with a clearance groove 19, and the second heat dissipation fins 12 are clearance-fitted with the clearance groove 19 to reserve movement clearance and reduce component collision and wear.

[0044] Example 2:

[0045] Based on the above embodiment one, the centrifugal airflow generation structure is optimized, and is now configured as follows.

[0046] See Figures 1-5 In the above embodiments, the centrifugal blades 17 are provided with twelve to eighteen blades to increase the flow rate of the circulating cooling airflow; the outer ring of the centrifugal impeller 16 is interference-fitted with the inner ring of the motor rotor to ensure that the impeller and the rotor rotate synchronously without relative displacement.

[0047] Example 3:

[0048] Based on the above embodiment one, to adapt to the heat dissipation load requirements of motors with different power, the following settings are now implemented.

[0049] See Figures 2-6 In the above embodiments, each group of first heat dissipation fins 6 consists of 40 to 60 first heat dissipation fins 6 stacked together, with four groups totaling 160 to 214 first heat dissipation fins 6, used for 2kW to 5kW motors to match the heat generation of small and medium power models; each group of first heat dissipation fins 6 consists of 70 to 100 first heat dissipation fins 6 stacked together, with four groups totaling 280 to 400 first heat dissipation fins 6, used for 6kW to 15kW motors to increase the heat exchange area to adapt to high power and high temperature operating conditions.

[0050] The implementation principle of this invention is as follows: First, when the UAV is powered on, the outer rotor rotates synchronously. The centrifugal impeller 16, which is interference-fitted with the inner ring of the outer rotor, rotates synchronously with the outer rotor. The centrifugal blades 17 integrally formed inside the centrifugal impeller 16 rotate synchronously and form a radially discharged positive pressure airflow inside the air duct 18. The number of centrifugal blades 17 can be adapted and adjusted according to the power requirements of the whole machine. The continuous flow of circulating airflow is generated by the rotation of the centrifugal blades 17. The airflow enters the fan-shaped heat dissipation hole 20 opened on the stator core 2 from the bottom position of the stator core 2, and continuously passes through the four sets of first heat dissipation fins 6 assembled in the heat dissipation hole 20 along the axial direction of the motor housing 1. During the airflow, it fully contacts and exchanges heat with the first heat dissipation fins 6, and carries away the heat accumulated by the iron loss generated by the alternating magnetization of the stator core 2.

[0051] The central shaft 14 is supported by two sets of angular contact support bearings 4 arranged face-to-face between the stator base 5 and the inner ring of the stator core 2. The two sets of angular contact bearings cooperate with each other to reduce the axial movement and radial sway of the central shaft 14 during the flight of the UAV, and reduce the frictional loss between the central shaft 14 and the stator core 2. The outer ring of the central shaft 14 is fitted with a bracket 15, and the top of the bracket 15 supports the centrifugal impeller 16. The centrifugal impeller 16 is detachably clamped and assembled by bolts screwed into the inner ring thread of the central shaft 14, which reduces the risk of the centrifugal impeller 16 falling off axially and continuously provides circulating cooling airflow for heat dissipation inside the motor.

[0052] Meanwhile, the stator winding 3 continuously generates copper heat during operation. The high thermal conductivity silicone grease filling the space between the stator winding 3 and the second heat sink fin 12 can quickly conduct the heat from the winding to the second heat sink fin 12. The second heat sink fin 12, with multiple ring arrays arranged in a ring, forms an overall heat dissipation structure by combining the bottom ring 11 and the top ring 13. It is arranged close to the top of the stator winding 3 to continuously dissipate the heat generated by the winding. The airflow that has completed heat exchange through the first heat sink fin 6 flows upward into the centrifugal impeller 16 and is then discharged radially outward along the motor. During the discharge process, it passes through the second heat sink fin 12, simultaneously cooling the second heat sink fin. 12. Air cooling heat exchange is carried out to simultaneously dissipate the heat generated by the two core heat sources, stator core 2 and stator winding 3, to alleviate the heat accumulation inside the motor, reduce the occurrence of enameled wire melting short circuit and irreversible demagnetization of magnets caused by high temperature, and reduce the probability of flight control overheat protection limiting the motor output pull; the bottom of the centrifugal blade 17 has a clearance groove 19, which is fitted with the second heat dissipation fin 12, top ring 13 and bottom ring 11 with clearance, which can reserve sufficient movement clearance, reduce the probability of the centrifugal blade 17 colliding and wearing with the heat dissipation structure on the stator side during rotation, and extend the service life of the heat dissipation components of the motor;

[0053] Throughout the airflow heat exchange process, the outer and inner bent fins 7 and 8, which are integrally formed on both sides of the single first heat dissipation fin 6, have different widths. The outer bent fin 7 is wider and the inner bent fin 8 is narrower. After multiple first heat dissipation fins 6 are stacked, they form a fan-shaped outline, which can fit tightly against the inner wall of the heat dissipation hole 20 in the fan-shaped cross-section, expanding the heat conduction contact area and improving the heat transfer efficiency. The multiple first heat dissipation fins 6 in a single group are interlocked by the interlocking buckles 9 and buckle plates 10 formed integrally on the upper and lower ends of the fins to achieve interlayer positioning. The buckling position can be reinforced by laser spot welding to reduce the possibility of the stacked fins separating from each other. The bottom of the outer bent fin 7 and the inner bent fin 8 is provided with a concave structure, which abuts against the positioning boss 21 formed integrally below the heat dissipation hole 20, forming a two-way constraint on the entire group of first heat dissipation fins 6 in the axial and radial directions. This reduces the phenomenon of fins falling off axially and moving radially under motor vibration conditions, and ensures the long-term stability of the heat exchange performance of the heat dissipation structure.

[0054] For heavy-duty drones with different power levels, the number of stacked first heat dissipation fins 6 in each group can be adjusted to form a suitable solution. Low-power models use fewer stacked fins, while high-power models increase the number of stacked fins to match the heat dissipation requirements under different operating conditions.

[0055] Although embodiments of the present invention have been shown and described, these specific embodiments are merely illustrative of the invention and are not intended to limit it. The specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. After reading this specification, those skilled in the art may make modifications, substitutions, and variations to the embodiments as needed without departing from the principles and spirit of the invention, provided that such modifications, substitutions, and variations are within the scope of the claims of the present invention and are protected by patent law.

Claims

1. An unmanned aerial vehicle motor comprising a housing (1), characterized in that: The inner ring of the outer shell (1) is connected to a stator core (2). The stator core (2) has four heat dissipation holes (20) at both ends. The lower part of each of the four heat dissipation holes (20) is integrally formed with a positioning boss (21). The four heat dissipation holes (20) are respectively connected with four sets of first heat dissipation fins (6). The two ends of each of the four sets of first heat dissipation fins (6) are integrally formed with a buckle (9) and a buckle plate (10). The two sides of each of the four sets of first heat dissipation fins (6) are integrally formed with an outer ring bent fin (7) and an inner ring bent fin (8). The stator core (2) has a stator winding (3) wrapped in the stator slot. The top of the stator winding (3) is connected to a bottom ring (11). The top is integrally formed with multiple second heat dissipation fins (12), and the top of the multiple second heat dissipation fins (12) is welded with a top ring (13); the bottom end of the stator core (2) is integrally formed with a stator base (5), and the inner ring of the stator base (5) and the stator core (2) are both connected with support bearings (4). The top ends of the two support bearings (4) are provided with a central shaft (14), and the outside of the central shaft (14) is connected with a centrifugal impeller (16) through a bracket (15). The centrifugal impeller (16) is integrally formed with centrifugal blades (17), and an air duct (18) is provided between the centrifugal impeller (16) and the centrifugal blades (17). The bottom of the centrifugal blades (17) is provided with a clearance groove (19).

2. The drone motor of claim 1, wherein: The thickness of the first heat dissipation fin (6) and the second heat dissipation fin (12) is 0.2 mm to 0.5 mm.

3. The drone motor of claim 1, wherein: The outer ring bent fin (7) and the inner ring bent fin (8) are both provided with an indentation on one side of their bottom, and the positioning boss (21) abuts against the indentation on one side of the bottom of the outer ring bent fin (7) and the inner ring bent fin (8).

4. The drone motor of claim 1, wherein: The width of the outer ring bent fin (7) is greater than the width of the inner ring bent fin (8). The heat dissipation hole (20) has a fan-shaped cross-section. The outer ring bent fin (7) and the inner ring bent fin (8) are tightly attached to the inner wall of the heat dissipation hole (20).

5. The drone motor of claim 2, wherein: The bottom ring (11) and the stator winding (3) are filled with high thermal conductivity silicone grease, and a plurality of second heat dissipation fins (12) are distributed in a ring array, with the second heat dissipation fins (12) and the clearance groove (19) in a gap fit.

6. The drone motor of claim 1, wherein: The two support bearings (4) are angular contact bearings and are arranged face to face.

7. The drone motor of claim 6, wherein: The inner ring of the central shaft (14) is threaded, and the centrifugal impeller (16) is detachably connected to the central shaft (14) by bolts.

8. The drone motor of claim 1, wherein: The centrifugal blades (17) are provided with twelve to eighteen blades, and the outer ring of the centrifugal impeller (16) is interference-fitted with the inner ring of the motor rotor.

9. The drone motor of claim 2, wherein: Each group of first heat dissipation fins (6) consists of forty to sixty first heat dissipation fins (6) stacked together, with four groups totaling one hundred and sixty to two hundred and fourteen first heat dissipation fins (6), for motors ranging from 2kW to 5kW.

10. The drone motor of claim 2, wherein: Each group of first heat dissipation fins (6) consists of seventy to one hundred first heat dissipation fins (6) stacked together, with four groups totaling two hundred and eighty to four hundred first heat dissipation fins (6), for motors ranging from 6kW to 15kW.

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