Natural air cooling motor of tilt-rotor vertical take-off and landing aircraft

Abstract

The invention relates to the technical field of motors, in particular to an inner rotor hollow natural air cooling motor of a tilt-rotor vertical take-off and landing aircraft, an electronic speed regulation and control device provides electric energy for an electromagnetic coil winding, an inner rotor rotates at a high speed under the action of electromagnetic force, the inner rotor is of a hollow transparent design, and the rotor drives a conical shell to rotate to suck air; air flows into the cavity of the inner rotor through the connecting block diversion trenches, and the surface of the cavity is subjected to groove treatment to increase the heat exchange area, quickly reduce the temperature of the inner rotor, improve the working stability and prolong the service life; hot air in the power part is exhausted through the engine shell, reverse thrust is generated at the same time, the power part does not need additional auxiliary heat dissipation devices in the operation process, heat can be dissipated automatically under the advantages of the shape and the structure of the power part, the motor is kept working in a reasonable temperature interval, the working stability of the motor is guaranteed, and the service life of the motor is prolonged.

Description

Technical Field

[0001] The invention relates to the technical field of motors, and in particular to a naturally air-cooled motor for a tilt-rotor vertical take-off and landing aircraft. Background Art

[0002] Electric aircraft refers to aircraft that are powered by electric motors instead of internal combustion engines. Electric aircraft use electric propulsion systems instead of internal combustion engines, which gives them many advantages and unique qualities. The most prominent advantages are energy saving and environmental protection, high efficiency, low energy consumption, near zero emissions, low noise and vibration levels, and good ride comfort. They are truly environmentally friendly aircraft. There are also many advantages in design: the overall layout is flexible, and the optimal layout and unconventional and innovative layouts can be adopted; aircraft with extraordinary performance can be designed to meet special purpose requirements, etc. Vertical take-off and landing aircraft do not need to taxi to take off and land.

[0003] This type of aircraft not only shows a wide range of application prospects in the fields of military, logistics, agriculture, etc., but is also considered an important means of transportation in the future in urban air traffic. In order to achieve efficient, stable and long-life operation of electric aircraft, higher requirements are placed on the performance of its core component, the motor. During the operation of the motor, the electromagnetic coil part and the electronic speed regulator are the main sources of heat. As the motor runs at high speed, the internal temperature will rise rapidly. If the heat cannot be taken out and dissipated in a timely and effective manner, the excessively high internal temperature of the motor will lead to problems such as reduced power and increased energy consumption. In particular, the magnetic properties of neodymium iron boron magnets decrease significantly at high temperatures, resulting in a decrease in the output power of the motor. At the same time, the increase in temperature may cause the thermal expansion and mechanical stress of the internal materials of the motor to increase, thereby affecting the accuracy and reliability of the motor.

[0004] In some existing natural air cooling systems, heat is usually dissipated by external air flow, but this method has certain limitations, especially when the aircraft is at low speed or hovering, the air flow is weak and the heat dissipation effect is poor. Summary of the invention

[0005] In order to overcome the deficiencies of the prior art, the present invention proposes an inner rotor hollow natural air-cooled motor, which achieves efficient heat dissipation through an optimized inner rotor structure and a self-exhaust method.

[0006] In order to achieve the above object, according to one aspect of the present invention, a hollow inner rotor natural air-cooled motor for a tiltrotor vertical take-off and landing aircraft is provided, comprising: a power source, the power source is composed of a power unit and a motor tail, the motor tail provides electrical energy to the power unit, and the power unit provides power to the propeller blades;

[0007] The motor end is fixedly connected to the power unit to transport cold air to the inside of the power unit and provide thrust for the aircraft.

[0008] Furthermore, the power unit includes an inner rotor, an inner wall of the inner rotor is provided with rifling grooves, the rifling grooves are evenly distributed on the inner wall of the inner rotor in a spiral shape, and the spiral shape of the rifling grooves is consistent with the direction of air flow.

[0009] Furthermore, a support frame is fixedly provided in the middle of the inner rotor, four evenly distributed guide groove curved connecting blocks are fixedly provided at the ends of the support frame, a plurality of heat sink brackets are fixedly provided on the inner ring of the inner rotor, and the heat sink brackets are fixedly connected to the outer surface of the support frame, a circle of heat dissipation copper mesh is fixedly provided on the outer ring of the inner rotor, a plurality of NdFeB magnet sheets are fixedly provided on the outer ring of the heat dissipation copper mesh, and a circle of carbon fiber rings are fixedly provided on both ends and the middle of the outer side of the NdFeB magnet sheets to protect the high-speed rotating inner rotor from being damaged.

[0010] Furthermore, a heat dissipation shaft is fixedly provided at the center of the inner rotor, a fixed fan blade is provided at the end of the heat dissipation shaft, the center of the fixed fan blade is rotatably connected to the heat dissipation shaft, a rotating fan blade is fixedly provided at the tail of the shaft, and when the inner rotor rotates, the rotating fan blade is driven to rotate through the heat dissipation shaft.

[0011] Furthermore, bearings are fixedly sleeved at the front and rear ends of the inner rotor, an electromagnetic coil winding is arranged outside the bearing, the inside of the electromagnetic coil winding is fixedly connected to the outside of the bearing, and a motor housing is fixedly arranged outside the electromagnetic coil winding.

[0012] Furthermore, the motor end is located at the front end of the power unit, and the motor end includes a blade disk.

[0013] Furthermore, a support frame socket is fixedly provided at the front end of the inner part of the blade disk, and sockets are provided around the support frame socket. The shape and number of the sockets are the same as those of the guide groove curved surface connection block.

[0014] Furthermore, a propeller blade is fixedly provided on the outer side of the blade disk, and the middle part of the propeller blade is hollowed out to reduce its own weight while ensuring its strength.

[0015] Furthermore, a conical shell is fixedly provided at the front end of the blade disk, a top cover is fixedly provided at the top end of the conical shell, and a penetrating trapezoidal hole is provided in the conical shell body. Two side edges of the trapezoidal hole and the front and rear end surfaces of the conical shell are parallel to each other, and the angles between the other two side edges and the front and rear end surfaces of the conical shell are acute angles, so that cold air is sucked into the power unit.

[0016] Furthermore, the tail of the motor includes an electronic speed control and controller and an engine casing. The electronic speed control and controller is fixed inside the engine casing to provide electrical energy for the electromagnetic coil winding. The bottom of the engine casing is a flat line and protrudes from the wing of the aircraft. A number of tail pipe heat dissipation stripes are fixed on the bottom surface of the engine casing.

[0017] Compared with the prior art, the present invention has the following beneficial effects: the electronic speed regulation and controller provides electric energy for the electromagnetic coil winding, and the electromagnetic coil winding generates a magnetic field after being energized, and the inner rotor is made of permanent magnets, which interact with the magnetic field of the electromagnetic coil winding to generate repulsive force, and the electromagnetic coil winding is fixed by the motor shell for the stator and cannot rotate; the top cover at the end of the conical shell is in a smooth arc shape, which reduces air resistance and improves the forward speed; when the propeller blades rotate, the trapezoidal holes on the conical shell are driven to rotate at the same time, and the high-speed rotating trapezoidal holes continuously cut the air, and the cold air is sucked into the inside of the conical shell, and flows into the cavity of the inner rotor through the gap of the guide groove curved surface connecting block, and exchanges heat with the inner rotor, thereby reducing the temperature of the inner rotor, improving its working stability, and extending its service life; the hot air in the power unit is discharged through the engine casing, and at the same time, reverse thrust is generated to push the motor forward and improve the motor power. The power unit does not require additional auxiliary heat dissipation equipment during operation, and can dissipate heat by itself under the advantages of its own shape and structure, thereby ensuring the working stability of the motor and extending its service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is an overall schematic diagram of the present invention;

[0019] Figure 2 It is a schematic diagram of the structure of the power unit of the present invention;

[0020] Figure 3 The motor end structure of the present invention is shown in FIG. Figure 1 ;

[0021] Figure 4 The motor end structure of the present invention is shown in FIG. Figure 2 ;

[0022] Figure 5 It is a schematic diagram of the electromagnetic coil winding and housing structure of the present invention;

[0023] Figure 6 It is an enlarged schematic diagram of the connection between the power unit and the motor end of the present invention;

[0024] Figure 7 It is an overall schematic diagram of the electronic speed regulation and controller of the present invention;

[0025] Figure 8 This is an overall schematic diagram of the heat dissipation shaft of the present invention;

[0026] Fig. 9 This is a schematic diagram of the motor housing structure of the present invention;

[0027] Fig.10 This is a schematic diagram of the inner rotor structure of the present invention;

[0028] Fig.11 This is a schematic diagram of the support structure of the present invention;

[0029] Fig.12 It is a schematic diagram of the structure of the engine casing of the present invention.

[0030] Illustration Description:

[0031] 1. Power unit; 101. Inner rotor; 102. Carbon fiber ring; 103. Bearing; 104. Electromagnetic coil winding; 105. Motor housing; 106. Rifling groove; 107. Support frame; 108. Heat sink bracket; 109. Heat dissipation copper mesh; 110. NdFeB magnet sheet; 111. Heat dissipation hole;

[0032] 2. Motor end; 201. Conical shell; 202. Top cover; 203. Blade disk; 204. Propeller blade; 205. Guide groove curved surface connection block; 206. Trapezoidal hole; 2031. Support frame socket; 2032. Socket;

[0033] 3. Motor tail; 301. Electronic speed regulation and controller; 303. Tail pipe heat dissipation stripes; 304. Heat dissipation shaft; 305. Fixed fan blades; 306. Rotating fan blades; 307. Engine casing. DETAILED DESCRIPTION

[0034] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined invention purpose, the specific implementation mode, structure, characteristics and effects of the present invention are described in detail below in combination with the accompanying drawings and preferred embodiments.

[0035] See also Figures 1 to 12 , This embodiment provides a naturally air-cooled motor for a tilt-rotor vertical take-off and landing aircraft, including: a power source, the power source is composed of a power unit 1 and a motor tail 3, the motor tail 3 provides electrical energy to the power unit 1, and the power unit 1 provides power for the propeller blades 204;

[0036] The motor end 2 is fixedly connected to the power unit 1 to deliver cold air to the inside of the power unit 1. When the power unit 1 is running, the trapezoidal hole 206 of the motor end 2 draws cold air into the inner rotor 101 to dissipate heat and provide thrust for the aircraft.

[0037] The power unit 1 includes an inner rotor 101, the inner wall of the inner rotor 101 is provided with rifling grooves 106, the rifling grooves 106 are evenly distributed on the inner wall of the inner rotor 101 in a spiral shape, and the spiral shape of the rifling grooves 106 is consistent with the direction of air flow, thereby increasing the contact area between the air and the inner wall and enhancing the heat dissipation capacity.

[0038] The surface of the rifling groove 106 is coated with a layer of anti-corrosion spray paint to improve its corrosion resistance;

[0039] A support frame 107 is fixedly provided in the middle of the inner rotor 101, and four evenly distributed guide groove curved surface connection blocks 205 are fixedly provided at the ends of the support frame 107. A plurality of heat sink brackets 108 are fixedly provided in the inner ring of the inner rotor 101, and the heat sink brackets 108 are fixedly connected to the outer surface of the support frame 107. A circle of heat dissipation copper mesh 109 is fixedly provided in the outer ring of the inner rotor 101, and a plurality of NdFeB magnet sheets 110 are fixedly provided in the outer ring of the heat dissipation copper mesh 109. A circle of carbon fiber ring 102 is fixedly provided at both ends and in the middle of the outer side of the NdFeB magnet sheet 110 to protect the high-speed rotating inner rotor 101 from being damaged. When the inner rotor 101 rotates at high speed, a strong ion The high-strength carbon fiber ring 102 tightly wraps the inner rotor 101 to offset its centrifugal force and prevent the inner rotor 101 from disintegrating and being damaged under the action of centrifugal force. The inner rotor 101 is stacked with high-performance NdFeB magnet sheets. According to different sizes and performance requirements, the number of stacked layers of magnet sheets is 1-3. The surface of the magnet is coated with protective insulating material to reduce the generation of eddy currents. Under the magnet is an integrated cylindrical annular heat dissipation copper mesh 109. The magnet and the heat dissipation copper mesh 109 are fixed by organic silicone glue to enhance the stability of the magnet and reduce vibration. The magnet and the heat dissipation copper mesh 109 are stacked together on a support frame 107 made of high-strength aluminum alloy.

[0040] It should be noted that mesh holes are distributed on the surface of the heat dissipation copper mesh 109, and the NdFeB magnet sheets 110 are arranged in a ring shape on the periphery of the heat dissipation copper mesh 109, and there is a gap between two adjacent NdFeB magnet sheets 110, so that air flow can escape from the gap between the heat dissipation copper mesh 109 and the NdFeB magnet sheets 110 to take away heat.

[0041] A circle of elliptical heat dissipation holes 111 is provided inside the heat sink bracket 108. The heat dissipation holes 111 are elliptical and have smooth inner walls, which are conducive to the flow of air inside the inner rotor 101. The airflow will quickly converge when entering the heat dissipation holes 111, thereby increasing the flow rate and accelerating the cooling rate. Not only that, the design of the heat dissipation holes 111 can also effectively reduce the weight of the heat sink bracket 108, making the motor as a whole lighter. At the same time, the design of the elliptical heat dissipation holes 111 can also increase the mechanical strength of the heat sink bracket 108 and avoid cracks on its lower surface during high-speed rotation; the heat dissipation copper mesh 109 wraps the magnet inside to prevent the magnet from vibrating when the motor rotates at high speed, thereby reducing the stability of the motor.

[0042] A heat dissipation shaft 304 is fixedly provided at the center of the inner rotor 101, and the inner rotor 101 drives the heat dissipation shaft 304 to rotate. A fixed fan blade 305 is provided at the end of the heat dissipation shaft 304. The center of the fixed fan blade 305 is rotatably connected to the heat dissipation shaft 304, and a rotating fan blade 306 is fixedly provided at the tail of the heat dissipation shaft 304. When the inner rotor 101 rotates, the rotating fan blade 306 is driven to rotate through the heat dissipation shaft 304 to discharge the hot air inside the power unit 1 to dissipate heat.

[0043] The front and rear ends of the inner rotor 101 are fixedly sleeved with bearings 103, which connect the inner rotor 101 with the electromagnetic coil winding 104 so that the inner rotor 101 and the electromagnetic coil winding 104 can generate relative rotation. The electromagnetic coil winding 104 is sealed by glue injection, and the outer layer is sleeved with a motor shell 105 coated with a magnetic shielding material. The motor shell 105 is made of aluminum alloy, which can improve the overall stability of the structure of the power unit 1. The outer ring of the bearing 103 is provided with an electromagnetic coil winding 104, and the inside of the electromagnetic coil winding 104 is fixedly connected to the outer ring of the bearing 103, while the inner ring of the bearing 103 is fixed to the inner rotor 101, so that the electromagnetic coil winding 104 can drive the inner rotor 101 to rotate without moving itself, and at the same time, a stable connection between the two can be ensured. The outside of the electromagnetic coil winding 104 is fixedly provided with a motor shell 105, and the motor shell 105 is fixedly connected to the front and rear end bearings 103 by rivets, which separates the electromagnetic coil winding 104 from the outside and protects the electromagnetic coil winding 104 from being damaged by external forces.

[0044] It should be noted that the electromagnetic coil winding 104 is composed of an electromagnetic coil and a silicon steel sheet. The electromagnetic coil is wound on the silicon steel sheet. When the electromagnetic coil is energized, it generates a magnetic field to drive the inner rotor 101 to rotate. The silicon steel sheet protects the electromagnetic coil. The electromagnetic coil winding 104 is fixed inside the motor housing 105, and the motor housing 105 is fixed inside the wing of the aircraft.

[0045] The motor end 2 is located at the front end of the power unit 1, and the motor end 2 includes a blade disk 203. A support frame socket 2031 is fixedly provided at the front end of the blade disk 203, and the support frame 107 can be matched and inserted into the support frame socket 2031. A socket 2032 is provided around the support frame socket 2031. The shape and number of the socket 2032 are the same as those of the guide groove curved surface connection block 205. The guide groove curved surface connection block 205 is inserted into the socket 2032 and fastened with rivets to connect the power unit 1 and the motor end 2 to prevent shaking in the socket 2032 and affect the stability of the motor.

[0046] A propeller blade 204 is fixedly provided on the outside of the blade disk 203. The middle part of the propeller blade 204 is hollowed out to reduce its own weight while ensuring strength. Air is sucked in from the outside of the propeller blade 204 and the hollow part. The propeller blade 204 is elliptical as a whole and has a flat surface. When the propeller blade 204 rotates, the elliptical blade disturbs more air. When the air impacts the surface of the propeller blade 204, it slides along its flat surface, reducing the reaction force of the air and enhancing the structural strength of the propeller blade 204.

[0047] A conical shell 201 is fixedly provided at the front end of the blade disk 203, and a top cover 202 is fixedly provided at the top end of the conical shell 201. The top cover 202 is in a smooth arc shape to reduce air resistance and increase forward speed. The body of the conical shell 201 is provided with a penetrating trapezoidal hole 206. Two side edges of the trapezoidal hole 206 are parallel to the front and rear end surfaces of the conical shell 201, and the other two side edges are in a curved shape. When the airflow passes through the trapezoidal hole 206, due to the setting of the curved hole wall, the airflow will automatically flow along the curved hole wall. Since the conical shell 201 is in a continuous rotating state, the airflow passing through the curved hole wall of the trapezoidal hole 206 can form a spiral airflow under high-speed rotation. Moreover, the curved hole wall of the trapezoidal hole 206 has a bending radius of 120°. This bending radius setting can effectively cause the airflow to change direction. And finally, it is conducive to the formation of spiral airflow, taking away more heat from the inner rotor 101, sucking cold air into the power unit 1, and the high-speed rotating trapezoidal hole 206 continuously cuts the air, sucking cold air into the conical shell 201 to form multiple spiral airflows, which flow into the cavity of the inner rotor 101 through the gap of the guide groove curved surface connecting block 205, and the spiral airflow formed by the trapezoidal hole 206 enters the rear spiral rifling groove 106 and just matches the shape of the rifling groove 106, so that the airflow can better pass through the rifling groove 106 and be consistent with the groove body, accelerate the flow speed of the air, extend the flow path of the air inside the inner rotor 101, make the air fully exchange heat with the inner rotor 101, reduce the temperature of the inner rotor 101, improve its working stability, and extend its service life;

[0048] The motor tail 3 includes an electronic speed control and controller 301 and an engine casing 307. The electronic speed control and controller 301 is fixedly arranged inside the engine casing 307. The outer end of the fixed fan blade 305 is fixedly connected to the engine casing 307 to provide electrical energy for the electromagnetic coil winding 104. The engine casing 307 wraps the inner rotor 101, the electromagnetic coil winding 104, and the motor casing 105, and is fixed to the motor casing 105 to guide the hot air inside the power unit 1 for heat dissipation. The bottom of the engine casing 307 is a flat line and protrudes from the wing of the aircraft, reducing the height of the engine casing 307 protruding from the outer end of the wing, ensuring heat dissipation while preventing rain from entering the power unit 1 and damaging internal accessories. The engine casing 307 adopts an integrated molding technology to enhance its structural strength. A number of tail pipe heat dissipation stripes 303 are fixedly arranged on the bottom surface of the engine casing 307 to guide the hot air inside the engine casing 307 out and enhance the heat dissipation effect.

[0049] The electronic speed regulation and controller 301 provides electric energy to the electromagnetic coil winding 104. The electromagnetic coil winding 104 generates a magnetic field after being energized. The inner rotor 101 is made of an aluminum alloy with a high-strength permanent magnet. The magnetic field generated by the inner rotor 101 interacts with the magnetic field generated by the electromagnetic coil winding 104 to generate a repulsive force, which drives the inner rotor 101 to rotate. The electromagnetic coil winding 104 is fixed by the motor housing 105 and cannot rotate. However, the inner rotor 101 rotates at a high speed under the action of the repulsive force. Since the motor end 2 is fixedly connected to the inner rotor 101 through the heat dissipation shaft 304, the motor end 2 rotates with the inner rotor 101. When the propeller blades 204 of the motor end 2 rotate The air flow is disturbed, and the air in front is pressed backward. Under the reaction force of the air, the propeller blades 204 generate forward thrust, pushing the aircraft forward; the top cover 202 at the end of the conical shell 201 is in a smooth arc shape, which reduces the friction resistance between it and the air and reduces the energy consumption of the propeller blades 204 to overcome the air resistance. When the propeller blades 204 rotate, the trapezoidal holes 206 on the conical shell 201 are driven to rotate at the same time. The high-speed rotating trapezoidal holes 206 continuously cut the air and divide the air into small portions with the same size and number as the trapezoidal holes 206. Due to the effect of inertia, the air continues to maintain its original state of motion, but relative to the conical shell 201 flying forward, the air moves backward. The air flows into the conical shell 201 through the support frame 107, flows into the cavity of the inner rotor 101, exchanges heat with the inner wall of the inner rotor 101, and reduces the temperature of the inner rotor 101. Since the inner wall of the trapezoidal hole 206 is inclined, it has a guiding effect on the air flowing through it, so the air flow flowing into the conical shell 201 through the trapezoidal hole 206 flows inward in a spiral shape. Moreover, the two sides of the trapezoidal hole 206 are curved. When the airflow passes through the trapezoidal hole 206, due to the setting of the curved hole wall, the airflow will automatically flow along the curved hole wall. Moreover, since the conical shell 201 is in a continuous rotating state, it can promote the airflow passing through the trapezoidal hole 206 in a high-speed rotating state. 6 The airflow of the curved hole wall forms a spiral airflow. Moreover, the curvature of the curved hole wall of the trapezoidal hole 206 is 120°. The setting of this curvature can effectively promote the airflow to change direction and ultimately facilitate the formation of a spiral airflow. The spiral shape of the rifling groove 106 on the inner wall of the inner rotor 101 is consistent with the direction of the air flow, which reduces the disturbance of the inner wall of the rifling groove 106 to the air, reduces the friction resistance between the two, speeds up the flow of air, increases the air flow rate flowing through the inner rotor 101 per unit time, enables the inner rotor 101 to exchange heat with more air, improves the heat exchange rate, reduces the temperature of the inner rotor 101, and ensures the stability of the operation of the air-cooled motor;The inner rotor 101 drives the rotating blades 306 to rotate through the heat dissipation shaft 304. When the rotating blades 306 rotate, negative pressure is generated in front of them. Under the action of the air pressure difference, the air in the cavity of the inner rotor 101 that has exchanged heat with the inner rotor 101 flows toward the engine casing 307, further accelerating the speed of the air flow inside the inner rotor 101 and improving the heat dissipation effect of the inner rotor 101. The air inside the inner rotor 101 is finally discharged to the outside of the air-cooled motor, while taking away the heat of the inner rotor 101. In this cycle, the inner rotor 101 is continuously cooled to ensure that the inner rotor 101 is in a Stable operation at low temperature; when the air inside the inner rotor 101 flows through the engine housing 307, it is guided by the tail pipe heat dissipation stripes 303 again, preventing the air from generating eddy currents in the engine housing 307 and hindering the circulation of the air in the inner rotor 101, ensuring that the air flows out of the engine housing 307 smoothly and quickly, taking away the heat of the inner rotor 101 and reducing the temperature of the inner rotor 101; the air-cooled motor does not require additional auxiliary heat dissipation equipment during operation, and can dissipate heat by itself under the advantages of its own shape and structure, so that the motor works at a low temperature and ensures the working stability of the motor. ;

[0050] The above are only preferred embodiments of the present invention, and are not intended to limit the present invention in any form. Although the present invention has been disclosed as above in the form of preferred embodiments, it is not intended to limit the present invention. Any technical personnel in the field can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any brief modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. An inner rotor hollow natural air-cooled motor for a tilt-rotor vertical take-off and landing aircraft, It is characterized in that include: A power source, the power source comprising a power part (1) and a motor tail part (3), the motor tail part (3) providing electrical energy to the power part (1), and the power part (1) providing power to the propeller blades (204); The motor end (2) is fixedly connected to the power unit (1) to transport cold air to the inside of the power unit (1) and provide thrust for the aircraft.

2. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 1, It is characterized in that The power unit (1) comprises an inner rotor (101), the inner wall of the inner rotor (101) being provided with rifling grooves (106), the rifling grooves (106) being evenly distributed on the inner wall of the inner rotor (101) in a spiral shape, and the spiral shape of the rifling grooves (106) being consistent with the direction of air flow.

3. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 2, It is characterized in that A support frame (107) is fixedly provided in the middle of the inner rotor (101), and four uniformly distributed guide groove curved surface connection blocks (205) are fixedly provided at the ends of the support frame (107). A plurality of heat sink brackets (108) are fixedly provided on the inner ring of the inner rotor (101), and the heat sink brackets (108) are fixedly connected to the outer surface of the support frame (107). A circle of heat dissipation copper mesh (109) is fixedly provided on the outer ring of the inner rotor (101), and a plurality of neodymium iron boron magnet sheets (110) are fixedly provided on the outer ring of the heat dissipation copper mesh sheet (109). A circle of carbon fiber ring (102) is fixedly provided at both ends and in the middle of the outer sides of the neodymium iron boron magnet sheets (110) to offset the centrifugal force generated by the high-speed rotating inner rotor (101).

4. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 3, It is characterized in that A heat dissipation shaft (304) is fixedly provided at the center of the inner rotor (101), a fixed fan blade (305) is provided at the end of the heat dissipation shaft (304), the center of the fixed fan blade (305) is rotatably connected to the heat dissipation shaft (304), and a rotating fan blade (306) is fixedly provided at the tail of the heat dissipation shaft (304), and when the inner rotor (101) rotates, the rotating fan blade (306) is driven to rotate through the heat dissipation shaft (304).

5. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 4, It is characterized in that The front end and the rear end of the inner rotor (101) are both fixedly sleeved with bearings (103), the outside of the bearing (103) is provided with an electromagnetic coil winding (104), the inside of the electromagnetic coil winding (104) and the outside of the bearing (103) are both fixedly connected, and the outside of the electromagnetic coil winding (104) is fixedly provided with a motor housing (105).

6. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 5, It is characterized in that The motor end (2) is located at the front end of the power unit (1), and the motor end (2) comprises a blade disk (203).

7. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 6, It is characterized in that A support frame insertion hole (2031) is fixedly provided at the front end of the inner part of the blade disk (203), and sockets (2032) are provided around the support frame insertion hole (2031). The shape and number of the sockets (2032) are the same as those of the guide groove curved surface connection block (205).

8. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 7, It is characterized in that A propeller blade (204) is fixedly provided on the outer side of the blade disk (203), and the middle part of the propeller blade (204) is hollowed out, thereby reducing its own weight while ensuring its strength.

9. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 8, It is characterized in that A conical shell (201) is fixedly provided at the front end of the blade disk (203), a top cover (202) is fixedly provided at the top end of the conical shell (201), and a penetrating trapezoidal hole (206) is provided in the body of the conical shell (201), two side edges of the trapezoidal hole (206) and the front and rear end surfaces of the conical shell (201) are parallel to each other, and the angles between the other two side edges and the front and rear end surfaces of the conical shell (201) are acute angles, so that cold air is sucked into the interior of the power unit (1).

10. The inner rotor hollow natural air-cooled motor of a tilt-rotor vertical take-off and landing aircraft according to claim 9, It is characterized in that The motor tail (3) comprises an electronic speed control and controller (301) and an engine casing (307). The electronic speed control and controller (301) is fixedly arranged inside the engine casing (307) to provide electric energy for the electromagnetic coil winding (104). The bottom of the engine casing (307) is in the form of a flat line and protrudes from the wing of the aircraft. A plurality of tail pipe heat dissipation stripes (303) are fixedly arranged on the bottom surface of the engine casing (307).

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