An eVTOL aircraft disc motor integrated propeller and control method

Abstract

The application discloses an eVTOL aircraft disc motor integrated propeller and a control method, and relates to the technical field of eVTOL aircrafts, and aims to improve the power density of the motor and ensure stable and efficient operation of the motor.

Description

Technical Field

[0001] This invention relates to the field of aviation power plant technology, specifically to an eVTOL aircraft disc motor integrated propeller and control method. Background Technology

[0002] Electric vertical takeoff and landing (eVTOL) aircraft, as the core carrier of future urban air mobility, have become an important development direction for solving urban congestion and realizing green travel due to their advantages of low noise, zero emissions and high maneuverability.

[0003] As the "heart" of eVTOL, the electric motor plays a crucial role in converting electrical energy into mechanical energy, providing the thrust required for flight, and realizing maneuver control. Its power density, heat dissipation efficiency, and operational stability are directly related to the aircraft's endurance, payload level, and flight safety.

[0004] As the energy density of eVTOL motors continues to increase, meaning the output power per unit volume gradually increases, the heat generated by the windings also increases accordingly, significantly raising the motor's heat dissipation pressure. Under high load operation, the motor generates a large amount of heat that easily accumulates. Prolonged operation can lead to stator winding overheating, magnetic performance degradation, and even motor damage, affecting flight safety.

[0005] Therefore, improving the heat dissipation efficiency of eVTOL motors is a technical problem that urgently needs to be solved. Summary of the Invention

[0006] The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose an eVTOL aircraft disc motor integrated propeller and control method to solve the technical problem of insufficient heat dissipation efficiency of eVTOL motors in the prior art.

[0007] To achieve the above-mentioned technical objectives, the present invention adopts the following technical solution: In a first aspect, the present invention provides an eVTOL aircraft disc motor integrated propeller, comprising: Base; The power module includes a stator, two rotors and two blades. The stator is coaxially embedded in the base and has several air guide holes along the axial direction. The two rotors are rotatably mounted on both ends of the base and coupled to the stator. The two blades are respectively connected to the two rotors in a one-to-one transmission connection. Two covers are provided, each corresponding to one of the two rotors. The covers are placed around the outer periphery of the corresponding rotor and fixedly connected to the base. The outer periphery of the covers is provided with several ventilation holes that communicate with the internal cavity. A detection module, wherein the detection module is used to monitor environmental parameters; and The control module is connected to the detection module and the stator signal respectively, and the control module adjusts the operating power of the stator according to the collected environmental parameters.

[0008] In some embodiments, the rotor includes a turntable and a plurality of magnets. The turntable is rotatably mounted on the base. The turntable has a plurality of fan blades on its outer periphery, which are arranged at an angle. The plurality of magnets are uniformly mounted circumferentially on the end face of the turntable facing the stator.

[0009] In some embodiments, the stator includes a plurality of sector-shaped iron blocks, which are sequentially spliced ​​end to end to form a motor core, and a plurality of air guide holes are spaced apart between adjacent sector-shaped iron blocks, and a winding is wound on the core.

[0010] In some embodiments, the base includes a fixed shaft, a bearing, and a support frame. The iron core is embedded and fixed inside the support frame. The fixed shaft is coaxially arranged with the support frame. The inner ring of the bearing is sleeved on the outside of the fixed shaft. The outer ring of the bearing is coaxially fixedly connected with the rotor.

[0011] In some embodiments, the sector-shaped iron blocks are embedded in the fixed shaft of the base by an interference fit, and a plurality of air guide holes are evenly spaced between each sector-shaped iron block, and the winding is wound and installed on the outside of the iron core.

[0012] In some embodiments, the system further includes two output shafts, each corresponding to one of the two rotors. The housing has a shaft hole through which the output shafts are connected to the rotors.

[0013] In some embodiments, the detection module includes a temperature sensor, a humidity sensor, and a pressure sensor installed on the housing, and the temperature sensor, the humidity sensor, and the pressure sensor are all communicatively connected to the control module.

[0014] Secondly, the present invention also provides a control method for an eVTOL aircraft with a disc motor integrated propeller, comprising the following steps: Monitor winding temperature rise and acquire environmental data, including altitude and humidity data. The control module processes the data and determines whether the winding temperature exceeds the preset threshold. If it exceeds the threshold, it triggers thermal protection and alarms. If it does not exceed the threshold, it performs air density compensation based on environmental data and optimizes the current vector control to the optimal efficiency mode. Based on the status data and environmental data, the control module determines whether the winding temperature exceeds a preset threshold. If it does, it triggers a thermal protection mechanism and sends an alarm to the flight control system. If it does not exceed the threshold, it performs air density compensation based on the environmental data and optimizes the current vector control to switch to the optimal efficiency mode.

[0015] In some embodiments, the current vector control optimization step in the control method for the disc motor integrated propeller of an eVTOL aircraft specifically includes: The detection module acquires altitude, temperature, and humidity parameters and calculates the current air density. Based on the air density, it corrects the target thrust requirement of the motor, adjusts the field weakening range and torque-current ratio of the current vector control, so that the motor matches the thrust requirement and the sum of copper loss and iron loss is within the preset minimum range.

[0016] In some embodiments, the coordinated control steps of the two blades include: The control module monitors the phase difference between the two rotors in real time, and adjusts the phase difference between the two rotors in combination with the operating status data and environmental data. At the same time, it adjusts the output power of the stator to keep the thrust output of the two blades in dynamic balance.

[0017] Compared with existing technologies, the eVTOL aircraft disc motor integrated propeller provided by this invention effectively improves the motor's power density through a structure in which the stator is coaxially embedded in the base and the two rotors are symmetrically installed at both ends of the base and coupled to the stator. The dual rotors working together can output stronger power, adapting to the power requirements of eVTOL vertical take-off and landing, hovering, and other scenarios. Two covers cover the two rotors, which can protect the rotors from collisions and protect internal components. The communication connection between the control module, the detection module, and the stator realizes intelligent closed-loop control of motor operation. The detection module monitors environmental parameters in real time, providing accurate decision-making basis for the control module. The control module dynamically adjusts the stator power according to environmental parameters, so that the motor can maintain the optimal operating state under different environmental conditions (such as different temperatures, humidity, and altitudes). The air guide holes in the stator and the air vents on the outer periphery of the casing form a continuous airflow channel. When the rotor rotates, it can drive the airflow through the air guide holes and air vents. Since the two rotors rotate in opposite directions, the airflow can enter the casing through the air vent of one casing and exit through the airflow channel from the air vent of the other casing, achieving efficient heat dissipation of the stator windings and preventing the motor from overheating and causing performance degradation or damage during long-term high-load operation. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the external shape of the disc motor integrated propeller of the eVTOL aircraft provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the internal structure of the disc motor integrated propeller of the eVTOL aircraft provided in an embodiment of the present invention; Figure 3 This is an exploded view of the power module provided in an embodiment of the present invention; Figure 4 This is an internal cross-sectional view of the disc motor integrated propeller of the eVTOL aircraft provided in an embodiment of the present invention; Explanation of reference numerals in the attached drawings: Base 1, Fixed shaft 11, Bearing 12, Support frame 13, Power module 2, Stator 21, Sector-shaped iron block 211, Winding 212, Air vent 213, Rotor 22, Turntable 221, Fan blade 2211, Magnet 222, Cover 3, Vent hole 31, Shaft hole 32, Output shaft 4. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0020] To address the technical problem of insufficient heat dissipation efficiency of eVTOL motors, this invention provides an integrated propeller and control method for an eVTOL aircraft disc motor, which can improve motor power density, achieve efficient heat dissipation and stable operation, and meet the usage requirements of flight scenarios such as eVTOL vertical take-off and landing.

[0021] It should be noted that the eVTOL aircraft disc motor integrated propeller of the present invention is used for, but not limited to, the power drive of eVTOL aircraft, propulsion of small vertical take-off and landing equipment, etc. For ease of explanation, in this invention, only the application of the eVTOL aircraft disc motor integrated propeller to the eVTOL aircraft power system is used as an example for explanation. The principle of the eVTOL aircraft disc motor integrated propeller applied to other types of equipment is essentially the same as the principle applied to the eVTOL aircraft power system, and will not be described in detail here.

[0022] Please see Figures 1 to 3 The eVTOL aircraft's disc motor integrated propeller includes a base 1, a power module 2, two housings 3, a control module, and a detection module. The power module 2 includes a stator 21, two rotors 22, and two blades. The stator 21 is coaxially embedded in the base 1 and has several air guide holes 213 along its axial direction. The two rotors 22 are rotatably mounted at both ends of the base 1 and coupled to the stator 21. The two housings 3 are respectively positioned corresponding to the two rotors 22, covering the outer periphery of the corresponding rotors 22 and fixed to the base 1. The outer periphery of the housings 3 has several ventilation holes 31 communicating with the interior. The detection module monitors environmental parameters. The control module is connected to the detection module and the stator 21, and adjusts the operating power of the stator 21 according to the collected environmental parameters.

[0023] In the above embodiments, the eVTOL aircraft's disc motor integrated propeller, through a structure in which the stator 21 is coaxially embedded in the base 1 and the dual rotors 22 are symmetrically installed at both ends of the base 1 and coupled to the stator 21, effectively improves the motor's power density. The dual rotors 22 working together can output stronger power, adapting to the power requirements of eVTOL vertical take-off and landing, hovering, and other scenarios. The two covers 3 correspondingly cover the two rotors 22, which can not only protect the rotors 22 from collisions but also protect the internal components. The communication connection between the control module, the detection module, and the stator 21 realizes intelligent closed-loop control of the motor operation. The detection module monitors environmental parameters in real time, providing accurate decision-making basis for the control module. The control module dynamically adjusts the power of the stator 21 according to environmental parameters, enabling the motor to maintain optimal operating conditions under different environmental conditions (such as different temperatures, humidity, and altitudes). The air guide hole 213 on the stator 21 and the air vent 31 on the outer periphery of the cover 3 form a through airflow channel. When the rotor 22 rotates, it can drive the airflow through the air guide hole 213 and the air vent 31. Since the rotation directions of the two rotors 22 are exactly opposite, the airflow can enter the cover 3 through the air vent 31 of one of the covers 3, and after passing through the airflow channel, it can be discharged from the air vent 31 of the other cover 3, so as to achieve efficient heat dissipation of the stator 21 winding 212 and avoid performance degradation or damage caused by overheating when the motor is running under high load for a long time.

[0024] It is understandable that the alternating magnetic field generated at both ends of the energized stator 21 is symmetrically distributed. Therefore, the two rotors 22 rotate in opposite directions, which can cancel out the reaction torque generated by their respective rotations, ensuring the attitude stability of the eVTOL aircraft during vertical takeoff and landing and hovering. At the same time, this reverse cooperative working method allows for a more balanced electromagnetic coupling between the dual rotors 22 and the stator 21, increasing the motor power density and outputting stronger power in a compact disc structure, while also balancing the forces on the motor during operation and reducing operational vibration.

[0025] Furthermore, the stator 21 and rotor 22 in this application adopt a yokeless design, which can significantly reduce the overall structural weight of the motor and reduce the axial and radial dimensions of the motor, further improving the power density and lightweighting of the eVTOL aircraft's disc motor integrated propeller, and better adapting to the stringent requirements of eVTOL aircraft for weight reduction and compact space layout. The yokeless structure can reduce the magnetic circuit loss of the motor, improve the electromagnetic conversion efficiency between the stator 21 and rotor 22, and further enhance the ability of the dual rotors 22 to output power in synergy. At the same time, this design can optimize the internal space layout.

[0026] In some embodiments, the rotor 22 includes a turntable 221 and a plurality of magnets 222. The turntable 221 is rotatably mounted on the base 1. A plurality of fan blades 2211 are arranged on the outer periphery of the turntable 221. A plurality of magnets 222 are circumferentially mounted on the side of the turntable 221 facing the stator 21. The rotor 22 adopts a structure with a turntable 221, magnets 222, and fan blades 2211 on the outer periphery. The turntable 221 provides a stable mounting carrier for the magnets 222 and fan blades 2211, ensuring that the magnets 222 are evenly distributed circumferentially, making the electromagnetic coupling between the rotor 22 and the stator 21 more stable, improving the smoothness of motor operation, reducing vibration and noise, and meeting the requirements of low noise and low vibration of the motor during eVTOL flight. The fan blades 2211 are integrated with the rotor 22, eliminating the need for an additional cooling fan, simplifying the motor structure and reducing manufacturing costs. At the same time, the fan blades 2211 rotate synchronously when the rotor 22 rotates, which can accelerate the airflow inside the motor, further enhance the heat dissipation effect, and ensure the stable operation of the motor under high load conditions.

[0027] In some embodiments, the fan blades 2211 are angled. Compared to horizontally or vertically positioned fan blades 2211, angled fan blades 2211 generate stronger axial airflow when rotating. This not only more efficiently removes heat from inside the motor, improving heat dissipation efficiency, but also reduces airflow resistance, lowers energy loss during fan blade rotation, and avoids the fan blades 2211 placing an additional burden on the motor's power output. Simultaneously, the airflow generated by the angled fan blades 2211 forms a stable airflow field, reducing airflow turbulence during motor operation and further improving motor stability, thus adapting to the complex airflow environment during eVTOL high-altitude flight.

[0028] In some embodiments, the stator 21 includes a plurality of sector-shaped iron blocks 211, which are sequentially spliced ​​end to end to form an iron core, and a plurality of air guide holes 213 are spaced apart between the plurality of sector-shaped iron blocks 211, and the winding 212 is wound around the iron core. The stator 21 is formed by splicing several sector-shaped iron blocks 211 end to end to form an iron core. Compared with a monolithic iron core, the sector-shaped iron blocks 211 are easier to process and require less material, which can reduce manufacturing costs. At the same time, it is easy to flexibly adjust the number of sector-shaped iron blocks 211 according to the motor power requirements to adapt to different specifications of eVTOL equipment. The air guide holes 213 are spaced between the sector-shaped iron blocks 211 to make the air guide holes 213 more evenly distributed, ensuring more balanced heat dissipation of the stator 21 iron core and winding 212, avoiding local overheating and extending the service life of winding 212. The winding 212 is wound on the spliced ​​iron core. The splicing structure of the iron core does not affect the winding accuracy of winding 212, which can ensure the stability of the electromagnetic performance of stator 21 and improve the energy conversion efficiency of motor.

[0029] In some embodiments, the base 1 includes a fixed shaft 11, a bearing 12, and a support frame 13. An iron core is embedded in the support frame 13, the fixed shaft 11 and the support frame 13 are coaxially arranged, the inner ring of the bearing 12 is fitted onto the fixed shaft 11, and the outer ring of the bearing 12 is coaxially connected to the rotor 22. The base 1, through the structure of the support frame 13 fixing the iron core, the fixed shaft 11 being coaxially arranged with the support frame 13, and the bearing 12 connecting the fixed shaft 11 and the rotor 22, achieves precise coaxial positioning of the stator 21 and the rotor 22. This ensures a uniform air gap between the rotor 22 and the stator 21 during rotation, reduces electromagnetic losses, and improves the motor's operating efficiency. The bearing 12 makes the rotor 22 rotate more smoothly, reduces frictional losses, and decreases noise and vibration during motor operation. Simultaneously, the structural design of the fixed shaft 11 and the support frame 13 enhances the load-bearing capacity of the base 1, effectively withstanding the centrifugal force generated during rotor 22 rotation and the vibration and impact during eVTOL flight, thus improving the motor's structural stability and service life.

[0030] In some embodiments, two output shafts 4 are also included, each corresponding to one of the two rotors 22. The housing 3 has a shaft hole 32, through which the output shafts 4 are connected to the rotors 22. The two output shafts 4 are connected to the two rotors 22 respectively and extend to the outside through the shaft hole 32 of the housing 3, realizing bidirectional independent output of motor power. This allows for flexible adaptation to the dual-propeller drive or multi-propeller cooperative drive requirements of eVTOL, improving the controllability of eVTOL flight attitude. The design of the shaft hole 32 ensures the installation accuracy and smooth rotation of the output shafts 4, while also providing a certain degree of sealing at the connection between the output shafts 4 and the housing 3, preventing dust and moisture from entering the motor and protecting internal components. The direct connection of the output shafts 4 to the rotors 22 reduces power transmission links, lowers power loss, and ensures that the power output from the motor is efficiently transmitted to the load.

[0031] In some embodiments, the detection module includes a temperature sensor, a humidity sensor, and a barometric pressure sensor mounted on the housing 3, all of which are communicatively connected to the control module. The integrated detection module, with its communication with the control module, enables comprehensive monitoring of the motor's operating status and environmental parameters: the temperature sensor can capture the real-time temperature rise of the winding 212, promptly detecting overheating risks and providing accurate data for the thermal protection mechanism; the humidity sensor monitors ambient humidity, preventing moisture damage and short circuits to internal motor components caused by high humidity; the barometric pressure sensor acquires altitude data, providing a basis for motor power adjustment and thrust compensation; the collaborative operation of multiple sensors makes the control module's adjustments more precise and comprehensive, further enhancing the motor's ability to adapt to complex flight environments and ensuring stable flight of the eVTOL in different scenarios.

[0032] Understandably, for the environmental and operational status monitoring scenarios of eVTOL motors, the temperature sensor can be a high-precision digital temperature sensor, thermistor, or platinum resistance sensor adapted to the temperature rise detection of the motor winding 212. The humidity sensor can be a capacitive or integrated humidity sensing element to monitor the ambient humidity and avoid the risk of short circuit due to moisture. The barometric pressure sensor can be a microcomputer-controlled electro-pressure sensor to obtain altitude barometric pressure data. All three types of sensors are selected to be models that can communicate with the control module and are integrated and installed in the housing 3. Through the coordinated selection and deployment of multiple types of sensors, key parameters of temperature, humidity, and barometric pressure are comprehensively collected, providing data basis for motor thermal protection, power adjustment, and thrust compensation, improving the motor's adaptability to complex flight environments, and ensuring stable flight of eVTOL.

[0033] Furthermore, the present invention also provides a control method for an eVTOL aircraft with a disc motor integrated propeller, comprising the following steps: Monitor winding temperature rise and acquire environmental data, including altitude and humidity data. The control module processes the data and determines whether the winding temperature exceeds the preset threshold. If it exceeds the threshold, it triggers thermal protection and alarms. If it does not exceed the threshold, it performs air density compensation based on environmental data and optimizes the current vector control to the optimal efficiency mode. Based on the status data and environmental data, the control module determines whether the winding temperature exceeds a preset threshold. If it does, it triggers a thermal protection mechanism and sends an alarm to the flight control system. If it does not exceed the threshold, it performs air density compensation based on the environmental data and optimizes the current vector control to switch to the optimal efficiency mode.

[0034] In the above embodiments, the control method for the disc motor integrated with the propeller in the eVTOL aircraft achieves comprehensive and real-time monitoring of the motor's operating status by collecting motor status data and environmental data, ensuring that the control module can promptly grasp the changes in motor operating conditions and the environment. Through winding temperature threshold judgment and thermal protection alarm mechanism, it can effectively prevent winding damage due to overheating, extend the motor's service life, and send alarms to the flight control system, facilitating timely handling of anomalies by operators and ensuring eVTOL flight safety. Based on air density compensation and current vector control optimization using environmental data, the motor can switch to the optimal efficiency mode under different environmental conditions, reducing energy consumption, improving the eVTOL's endurance, and optimizing the motor's power output stability to meet the needs of different flight conditions such as eVTOL vertical takeoff and landing and aerial cruise.

[0035] In some embodiments, the control method for the disc motor integrated propeller of the eVTOL aircraft specifically includes the following current vector control optimization steps: The detection module acquires altitude, temperature, and humidity parameters and calculates the current air density. Based on the air density, it corrects the target thrust requirement of the motor, adjusts the field weakening range and torque-current ratio of the current vector control, so that the motor matches the thrust requirement and the sum of copper loss and iron loss is within the preset minimum range.

[0036] In the above embodiments, the current air density is calculated by using the altitude and temperature / humidity parameters obtained by the detection module, achieving precise adaptation to the motor's operating environment. Correcting the motor's target thrust requirement based on air density ensures that the motor's output thrust precisely matches the actual flight requirements of the eVTOL, avoiding insufficient thrust or excessive energy consumption. By adjusting the field weakening range and torque-current ratio of the current vector control, the motor meets thrust requirements while minimizing the sum of copper and iron losses, significantly improving the motor's energy utilization efficiency, further optimizing the eVTOL's range performance, and reducing wear on motor components, thus extending the motor's lifespan.

[0037] In some embodiments, the control module monitors the phase difference between the two rotors in real time, adjusts the phase difference between the two rotors in combination with the operating status data and environmental data, and simultaneously adjusts the output power of the stator to keep the thrust output of the two blades in dynamic balance.

[0038] To better understand this invention, the following is combined with... Figures 1 to 4 The technical solution of the present invention will be described in detail below: The eVTOL aircraft's disc motor integrated propeller mainly consists of a base 1, a power module 2, and two housings 3. The power module 2 includes a stator 21 and two rotors 22. The stator 21 is coaxially embedded in the base 1 and has several air vents 213. The two rotors 22 are symmetrically installed at both ends of the base 1 and coupled to the stator 21. The two housings 3 cover the rotors 22 and are fixed to the base 1. They have ventilation holes 31 on their outer periphery. The air vents 213 and ventilation holes 31 form a through airflow channel. The stator 21 winding 212 is efficiently cooled by the counter-rotation of the two rotors 22. At the same time, the housings 3 can protect the rotors 22 and prevent foreign objects from entering. The coordinated work of the two rotors 22 can also improve the power density and adapt to the needs of eVTOL vertical take-off and landing scenarios. The rotor 22 consists of a turntable 221, several magnets 222, and inclined fan blades 2211. The turntable 221 provides a mounting carrier for the magnets 222 and fan blades 2211, ensuring stable electromagnetic coupling and reducing vibration and noise. The integrated design of the fan blades 2211 and rotor 22 simplifies the structure, reduces costs, and enhances heat dissipation. The stator 21 is formed by splicing several fan-shaped iron blocks 211 end to end to form an iron core. Air guide holes 213 are spaced between the iron blocks, reducing processing costs, facilitating flexible adaptation to different specifications, and ensuring uniform heat dissipation. The base 1 includes a fixed shaft 11, bearings 12, and a support frame 13, achieving precise coaxial positioning of the stator 21 and rotor 22, reducing losses, improving stability, and extending service life. The motor is also equipped with two output shafts 4, which are connected to the rotor 22 through the shaft hole 32 of the cover 3 to achieve bidirectional independent power output, improve the controllability of eVTOL flight and reduce power loss. In addition, the control module communicates with the detection module that integrates temperature, humidity and air pressure sensors, and can dynamically adjust the stator 21 power according to environmental parameters to achieve intelligent closed-loop control and ensure stable and safe operation of the motor in complex environments.

[0039] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A disc motor integrated propeller for an eVTOL aircraft, characterized in that, include: Base; The power module includes a stator, two rotors and two blades. The stator is coaxially embedded in the base and has several air guide holes along the axial direction. The two rotors are rotatably mounted on both ends of the base and coupled to the stator. The two blades are respectively connected to the two rotors in a one-to-one transmission connection. Two covers are provided, each corresponding to one of the two rotors. The covers are placed around the outer periphery of the corresponding rotor and fixedly connected to the base. The outer periphery of the covers is provided with several ventilation holes that communicate with the internal cavity. The detection module is used to monitor environmental parameters; as well as The control module is connected to the detection module and the stator signal respectively, and the control module adjusts the operating power of the stator according to the collected environmental parameters.

2. The eVTOL aircraft disc motor integrated propeller according to claim 1, characterized in that, The rotor includes a turntable and several magnets. The turntable is rotatably mounted on the base. Several fan blades are provided on the outer periphery of the turntable. The fan blades are arranged at an angle. Several magnets are evenly mounted on the end face of the turntable facing the stator along the circumference.

3. The eVTOL aircraft disc motor integrated propeller according to claim 1, characterized in that, The stator includes several sector-shaped iron blocks, which are sequentially spliced ​​end to end to form a motor core. Several air guide holes are distributed at intervals between adjacent sector-shaped iron blocks, and windings are wound on the core.

4. The eVTOL aircraft disc motor integrated propeller according to claim 3, characterized in that, The base includes a fixed shaft, a bearing, and a support frame. The iron core is embedded and fixed inside the support frame. The fixed shaft is coaxially arranged with the support frame. The inner ring of the bearing is sleeved on the outside of the fixed shaft. The outer ring of the bearing is coaxially fixedly connected with the rotor.

5. The eVTOL aircraft disc motor integrated propeller according to claim 3, characterized in that, The sector-shaped iron blocks are embedded in the fixed shaft of the base with an interference fit. A number of air guide holes are evenly spaced between each sector-shaped iron block. The winding is wound and installed on the outside of the iron core.

6. The eVTOL aircraft disc motor integrated propeller according to claim 1, characterized in that, It also includes two output shafts, each corresponding to one of the two rotors. The housing has a shaft hole, through which the output shafts are connected to the rotors.

7. The eVTOL aircraft disc motor integrated propeller according to claim 1, characterized in that, The detection module includes a temperature sensor, a humidity sensor, and a pressure sensor installed on the housing, and the temperature sensor, the humidity sensor, and the pressure sensor are all communicatively connected to the control module.

8. A control method for an eVTOL aircraft disc motor integrated propeller, applied to the eVTOL aircraft disc motor integrated propeller as described in any one of claims 1 to 7, characterized in that, Includes the following steps: Monitor winding temperature rise and acquire environmental data, including altitude and humidity data. The control module processes the data and determines whether the winding temperature exceeds the preset threshold. If it exceeds the threshold, it triggers thermal protection and alarms. If it does not exceed the threshold, it performs air density compensation based on environmental data and optimizes the current vector control to the optimal efficiency mode. The control module determines whether the winding temperature exceeds a preset threshold based on the status data and environmental data. If the limit is exceeded, the thermal protection mechanism is triggered and an alarm is sent to the flight control system; If the limit is not exceeded, air density compensation is performed based on environmental data, and current vector control is optimized to switch to the optimal efficiency mode.

9. The control method for the disc motor integrated propeller of an eVTOL aircraft according to claim 8, characterized in that, The specific steps for optimizing current vector control are as follows: The detection module acquires altitude, temperature, and humidity parameters and calculates the current air density. Based on the air density, it corrects the target thrust requirement of the motor, adjusts the field weakening range and torque-current ratio of the current vector control, so that the motor matches the thrust requirement and the sum of copper loss and iron loss is within the preset minimum range.

10. The control method for the disc motor integrated propeller of an eVTOL aircraft according to claim 8, characterized in that, The coordinated control steps for the two blades include: The control module monitors the phase difference between the two rotors in real time, and adjusts the phase difference between the two rotors in combination with the operating status data and environmental data. At the same time, it adjusts the output power of the stator to keep the thrust output of the two blades in dynamic balance.

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