Aviation drive motor, aircraft propulsion device and aircraft

Abstract

The present application discloses an aviation drive motor, an aircraft propulsion device and an aircraft, wherein the aircraft propulsion device includes a duct, a ducted fan propeller arranged inside the duct and at least one aviation drive motor that provides power for the ducted fan propeller, and further includes a cooling unit, the cooling unit including a duct cooling mechanism and a motor cooling mechanism, the motor cooling mechanism including a motor housing and a cooling circulation mechanism arranged between the stator and the rotor of the aviation drive motor, and the cooling circulation mechanism is connected to the motor housing, and further includes a motor damping mechanism, the motor damping mechanism including a stator adjustment mechanism connected to the stator, the stator adjustment mechanism drives the stator to move axially to adjust the axial distance between the stator and the rotor. By adopting the above scheme, the power density of the electric propulsion aircraft propulsion device can be improved while also improving the stability of the motor structure in the electric propulsion aircraft propulsion device to ensure its power safety in the aircraft and thus ensure flight safety.

Description

Technical Field

[0001] The present application belongs to the field of aircraft technology, and in particular relates to an aviation drive motor, an aircraft propulsion device, and an aircraft. Background Art

[0002] With the continuous advancement of aviation technology, the performance requirements of modern aircraft are constantly increasing, placing more stringent standards on parameters such as power unit efficiency, weight, and size. Traditional aircraft power units are gradually showing limitations in these key indicators, making it difficult to meet the development needs of high performance and low energy consumption.

[0003] As an emerging technology in the field of electric motors, axial flux motors, with their outstanding advantages such as high power density, high efficiency, and compact structural design, provide new ideas and solutions for upgrading aircraft power systems. The introduction of axial flux motors into the aircraft field is expected to fundamentally break through the bottlenecks of traditional power units and achieve significant improvements in aircraft performance. However, due to their inherent structural characteristics, existing axial flux motors have problems with heat dissipation and low heat dissipation efficiency. Moreover, when axial flux motors are used in aircraft propulsion systems, as the aircraft's flight altitude increases, the air becomes thinner and the convective heat dissipation effect deteriorates, further increasing the heat dissipation difficulty of the motor. In addition, due to their structural characteristics, axial flux motors generate large centrifugal forces during operation, which intensify the vibration of the motor during operation. At the same time, their electromagnetic torque fluctuates relatively greatly, which also leads to increased motor vibration. This vibration may be transmitted to the aircraft's fuselage structure through the mounting bracket. Long-term accumulation may affect the structural stability of the aircraft, leading to problems such as loose components and fatigue damage.

[0004] This shows that the existing technology still has certain defects. Summary of the Invention

[0005] The present application provides an aviation drive motor, an aircraft propulsion device, and an aircraft to solve at least one of the above-mentioned technical problems.

[0006] The technical solutions adopted in this application are:

[0007] In a first aspect, the present application provides an aviation drive motor, which is provided in an aircraft propulsion device. The aircraft propulsion device includes a power mechanism and the aviation drive motor. The aviation drive motor is connected to the power mechanism to provide power to the power mechanism.

[0008] The aviation drive motor includes a motor cooling mechanism, which includes a motor housing and a cooling circulation mechanism arranged between the stator and rotor of the aviation drive motor. The stator includes a mounting disk and a plurality of coil windings arranged on the mounting disk. The plurality of coil windings are arranged at intervals along the circumference of the mounting disk. The cooling circulation mechanism is arranged in the air gap between the stator and the rotor and / or the gap between the plurality of coil windings, and the cooling circulation mechanism is connected to the motor housing. It also includes a motor vibration damping mechanism, which includes a stator adjustment mechanism connected to the stator. The stator adjustment mechanism drives the stator to move axially to adjust the axial distance between the stator and the rotor.

[0009] As a preferred embodiment of the present application, the motor housing includes an end cover, and the stator adjustment mechanism includes a driving member and a transmission member, the transmission member is respectively connected to the driving member, the mounting plate and the cooling jacket, and the driving member drives the mounting plate and the cooling jacket to move axially through the transmission member to adjust the size of the air gap between the stator and the rotor.

[0010] As a preferred embodiment of the present application, the cooling circulation mechanism includes a cooling jacket and circulation blades connected to the cooling jacket, the circulation blades are arranged around the circumference of the cooling jacket and the circulation blades are arranged corresponding to the gap between two adjacent coil windings, a first circulation passage for the flow of coolant is provided inside the cooling jacket, a second circulation passage for the flow of coolant is provided inside the circulation blades, the second circulation passage is connected to the first circulation passage, and the motor housing is also provided with an external circulation passage.

[0011] As a preferred embodiment of the present application, a plurality of mounting grooves are provided on the side of the mounting disk facing the stator, a cooling jacket mounting seat is provided in the middle of the mounting disk along the radial direction, the cooling jacket is provided in the mounting seat, a plurality of coil windings are correspondingly provided in the mounting grooves, and an air hole is provided between two adjacent mounting grooves, which passes through the mounting disk in the axial direction, the air hole extends radially along the mounting disk and the width of the air hole is greater than the thickness of the circulating blade, and the cooling circulation mechanism also includes a forced cooling fan provided on the side of the mounting disk away from the rotor, and the cooling air blown out by the forced cooling fan enters the air gap through the air hole and both sides of the circulating blade.

[0012] As a preferred embodiment of the present application, the cooling circulation mechanism also includes a centrifugal air flow channel, the rotor includes a rotor disk and a magnet arranged on the rotor disk, the centrifugal air flow channel is arranged on the side of the rotor disk facing the stator, and includes a plurality of radial grooves arranged radially, and a plurality of magnets are provided, and the plurality of magnets are arranged corresponding to the coil windings and are arranged at intervals along the circumference of the rotor disk, and the radial groove is provided in the gap between two adjacent magnets.

[0013] As a preferred embodiment of the present application, the radial groove includes a straight segment and a curved segment that are interconnected, and the curved segment is provided at an edge portion of the rotor disk along the radial direction of the rotor disk.

[0014] As a preferred embodiment of the present application, the motor housing is also provided with an air outlet corresponding to the air gap, the air outlet is connected to the air gap and the air duct, and one end of the air outlet connected to the air duct opens along the extension direction of the air duct toward the airflow outlet of the air duct.

[0015] As a preferred embodiment of the present application, the driving member is a micro-motor connected to the end cover of the motor housing, and the transmission member includes a screw that cooperates with the micro-motor and a connecting seat arranged on the screw and connected to the mounting plate and / or the cooling sleeve.

[0016] As a preferred embodiment of the present application, the motor vibration damping mechanism further includes a vibration damping connecting arm and a buffer layer arranged on the inner wall of the motor housing, and the two ends of the vibration damping connecting arm are respectively connected to the duct and the motor housing.

[0017] In a second aspect, the present application further provides an aircraft propulsion device, comprising a duct, a power mechanism disposed within the duct, and at least one aviation drive motor as described above, wherein the power mechanism is a ducted fan propeller, and the aviation drive motor is connected to the ducted fan propeller to provide power for the ducted fan propeller;

[0018] The aircraft propulsion device also includes a ducted cooling mechanism, the ducted cooling structure includes a liquid cooling device and a ducted cooling passage arranged inside the shell of the duct, a connecting passage is arranged inside the vibration-damping connecting arm, the ducted cooling passage and the connecting passage are both connected to the liquid cooling device, and the connecting passage is connected to the cooling circulation mechanism.

[0019] As a preferred embodiment of the present application, it also includes a monitoring unit and a control unit, the monitoring unit includes a temperature monitoring component for monitoring the temperature of the coil winding and a distance monitoring component for monitoring the size of the air gap, and the control unit is respectively connected to the monitoring unit, the liquid cooling device, and the stator adjustment mechanism.

[0020] In a third aspect, the present application also provides an aircraft comprising a fuselage, wings, landing gear and a power system, wherein the power system comprises at least two groups of propulsion units symmetrically arranged on both sides of the fuselage or on the wings on both sides of the fuselage, and each of the propulsion units comprises at least one aircraft propulsion device as described above.

[0021] Due to the adoption of the above technical solution, the beneficial effects achieved by this application are as follows:

[0022] 1. In the above solution, the cooperation between the duct cooling mechanism and the motor cooling mechanism can improve the heat dissipation efficiency and heat dissipation effect of the aircraft drive motor in the solution of this application, thereby facilitating the high efficiency and stability of the aircraft drive motor during propulsion operation, thereby ensuring the high efficiency and stability of the aircraft propulsion device in the solution of this application during operation, and ultimately ensuring the flight safety of the aircraft;

[0023] 2. In the above solution, the motor cooling mechanism achieves both internal and external heat dissipation for the aircraft drive motor through the motor housing and the cooling circulation mechanism, while also achieving a highly efficient combination of liquid cooling and air cooling. This results in higher heat dissipation efficiency, and the structural arrangement of the entire cooling circulation mechanism can be effectively integrated with the inherent structure of the aircraft drive motor. This effectively improves heat dissipation efficiency while avoiding damage to the structural balance of the aircraft drive motor, thereby facilitating the reduction of vibrations generated during motor operation. Furthermore, the cooling of the ducted structure by the ducted cooling mechanism can improve the cooling efficiency of the entire aircraft propulsion device, thereby facilitating improved operating efficiency of the entire propulsion device.

[0024] 3. In the above solution, the stator adjustment mechanism is provided to adjust the distance between the stator and the rotor of the aircraft drive motor, that is, the air gap, thereby maintaining a stable distribution of the magnetic field in the air gap between the stator and the rotor, reducing electromagnetic force fluctuations and thus reducing vibrations generated during motor operation;

[0025] 4. In the above scheme, the provision of the vibration-absorbing layer and the vibration-absorbing connecting arm can further reduce the vibration transmitted from the motor to the duct and even other parts of the propulsion device, thereby helping to ensure the structural stability of the entire aircraft propulsion device;

[0026] 5. In the above scheme, by setting up a monitoring unit, real-time monitoring of the motor temperature and the stator-rotor spacing can be achieved. In conjunction with the control unit, the working status of the cooling unit and the stator adjustment mechanism can be adjusted in a timely and accurate manner to keep the entire aircraft propulsion device in the best working state, ensure the stability of the aircraft propulsion device, and thus help to ensure the flight safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0028] Figure 1 A schematic diagram of the structure of an aircraft propulsion device in an example;

[0029] Figure 2 A schematic diagram of a portion of the motor cooling mechanism in an example;

[0030] Figure 3 is a schematic diagram of the structure of a stator in an example;

[0031] Figure 4 is a schematic diagram of the structure of a rotor in an example;

[0032] Figure 5 is a schematic diagram of the coolant flow path in a cooling unit in an example;

[0033] Figure 6 This is a schematic diagram of the control between the monitoring unit, the control unit, the liquid cooling device and the stator adjustment mechanism in an example.

[0034] List of parts and reference numerals:

[0035] 1 ducted, 11 damping connection frame; 2 ducted fan propellers;

[0036] 3 Aviation drive motor, 31 motor housing, 311 air outlet, 312 buffer layer, 313 external circulation path, 32 stator, 321 mounting plate, 3211 mounting slot, 3212 cooling jacket mounting seat, 3213 air hole, 322 coil winding, 33 rotor, 331 rotor disk, 332 magnet, 333 centrifugal air flow channel, 3331 straight segment, 3332 curved segment, 34 air gap;

[0037] 41 cooling jacket, 411 first circulation path, 42 circulation blades, 421 second circulation path, 43 forced cooling fan;

[0038] 51 micro motor, 521 lead screw, 522 connecting seat;

[0039] 61 liquid cooling device, 62 connecting passage;

[0040] 7 monitoring unit, 71 temperature monitoring unit, 72 distance monitoring unit;

[0041] 8 control units. DETAILED DESCRIPTION

[0042] In order to more clearly illustrate the overall concept of the present application, a detailed description is given below in an illustrative manner in conjunction with the accompanying drawings.

[0043] The following description sets forth many specific details to facilitate a thorough understanding of the present application. However, the present application may also be implemented in other ways than those described herein, and therefore, the scope of protection of the present application is not limited by the specific embodiments disclosed below. It should be noted that the embodiments of the present application and the features of each embodiment may be combined with each other unless there is a conflict.

[0044] In addition, in the description of the present application, it should be understood that the terms "top", "bottom", "inside", "outside", "axial", "radial", "circumferential", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as limitations on the present application.

[0045] In this application, unless otherwise expressly specified or limited, terms such as "installed," "connected," "connect," and "fixed" should be understood in a broad sense. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0046] In this application, unless otherwise expressly specified and limited, a first feature "above" or "below" a second feature may be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in an appropriate manner in any one or more embodiments or examples.

[0047] Reference Figures 1-6 As shown, the present application discloses an aviation drive motor and an aircraft propulsion device. The aviation drive motor is applied to the aircraft propulsion device to provide power for the power mechanism of the aircraft propulsion device.

[0048] In one example, continue with Figure 1 As shown, the aircraft propulsion device in the present application includes a duct 1, a ducted fan propeller 2 is used inside the duct 1 as a power mechanism, and an aviation drive motor 3 is connected to the ducted fan propeller 2 to drive the ducted fan propeller 2 to rotate. In order to improve the heat dissipation capacity of the aviation drive motor in the present application so that it can be better applied to the aircraft propulsion device, and also as a preferred embodiment of the present application, the motor cooling mechanism of the aviation drive motor in the present application scheme includes a motor housing 31 and a cooling circulation mechanism arranged between the stator 32 and the rotor 33 of the aviation drive motor 3, the stator 32 includes a mounting disk 321 and a plurality of coil windings 322 arranged on the mounting disk 321, the plurality of coil windings 322 are arranged at intervals along the circumference of the mounting disk 321, the cooling circulation mechanism is arranged in the air gap 34 between the stator 32 and the rotor 33 and / or the gap between the plurality of coil windings 322, and the cooling circulation mechanism is connected to the motor housing 31, and also includes a motor vibration damping mechanism, the motor vibration damping mechanism includes a stator adjustment mechanism connected to the stator 32, the stator adjustment mechanism drives the stator 32 to move axially to adjust the axial distance between the stator 32 and the rotor 33.

[0049] In the above scheme, the use of the above-mentioned motor cooling mechanism can improve the heat dissipation efficiency and heat dissipation effect of the aviation drive motor 3 in the aircraft propulsion device, and by setting the stator adjustment mechanism, the distance between the stator 32 and the rotor 33 of the aviation drive motor 3 can be adjusted, that is, the air gap 34 can be adjusted to keep the distribution of the magnetic field in the air gap 34 between the stator 32 and the rotor 33 stable, reduce the electromagnetic force fluctuation and thus reduce the vibration generated during the operation of the motor, which is conducive to ensuring the high efficiency and stability of the aviation drive motor 3 during the propulsion process, and thus ensuring the high efficiency and stability of the entire aircraft propulsion device during operation, and ensuring the flight safety of the aircraft.

[0050] Further, refer to Figure 2 、 Figure 3As shown, the cooling circulation mechanism includes a cooling jacket 41 and circulating blades 42 connected to the cooling jacket 41. The circulating blades 42 are arranged around the circumference of the cooling jacket 41 and are arranged corresponding to the gaps between two adjacent coil windings 322. A first circulation passage 411 for the flow of coolant is provided inside the cooling jacket 41, and a second circulation passage 421 for the flow of coolant is provided inside the circulating blades 42. The second circulation passage 421 is connected to the first circulation passage 411, and the motor housing 31 is also provided with an external circulation passage 313. In the above scheme, the coolant enters the first circulation passage 411 and is diverted to each second circulation passage 421 through the first circulation passage 411 to perform heat exchange cooling on the stator 32 and the rotor 33 from the inside out. At the same time, the external circulation passage 313 inside the motor housing 31 is used to cool the entire motor structure inside and outside, greatly improving the heat dissipation efficiency of the motor to ensure its working efficiency and stability during the operation of the aircraft propulsion device.

[0051] In one example, continue with Figure 3 As shown, the mounting plate 321 is provided with a plurality of mounting grooves 3211 on the side facing the stator 32, and a cooling jacket mounting seat 3212 is provided in the middle of the radial mounting plate 321. The cooling jacket 41 is provided in the mounting seat, and a plurality of coil windings 322 are correspondingly provided in the mounting grooves 3211. The circulating blades 42 are provided in the middle of the interval between two adjacent mounting grooves 3211. This arrangement greatly reduces the difficulty of processing and manufacturing the motor stator 32, especially reduces the difficulty of manufacturing and uniformly arranging the coil windings 322, and can reserve space for the installation of the circulating blades 42, thereby improving assembly efficiency. Continue to refer to Figure 3 As shown, preferably, in this example, an air hole 3213 is provided between two adjacent mounting grooves 3211, which penetrates the mounting disk 321 axially. The air hole 3213 extends radially along the mounting disk 321 and the width of the air hole 3213 is greater than the thickness of the circulating blade 42. The cooling circulation mechanism also includes a forced cooling fan 43 arranged on the side of the mounting disk 321 away from the rotor 33. The cooling air blown out by the forced cooling fan 43 is blown toward one side of the rotor 33 through the air hole 3213, and after passing through the air hole 3213, it is diverted by the circulating blade 42 and enters the air gap 34 close to the coil winding 322 on both sides of the circulating blade 42.

[0052] At the same time, refer to Figure 2As shown, the motor housing 31 is also provided with a plurality of air outlets 311 arranged circumferentially around the motor housing 31 corresponding to the air gap 34. The air outlets 311 are connected to the air gap 34 and the air duct in the duct 1, and the end of the air outlet 311 connected to the duct 1 opens along the axial direction of the duct 1 toward the air duct outlet of the duct 1. In the above scheme, the cooling air flows along the path of the air hole 3213 - both sides of the circulation blade 42 - the air gap 34 - the air outlet 311 - the duct 1, which can increase the flow speed of the gas inside the motor and blow the cooled gas on both sides of the circulation blade 42 into the air gap 34 to assist in heat dissipation of the rotor 33. In the above scheme, the direction of the air outlet 311 is the same as the direction of gas discharge in the duct 1, thereby preventing the cooling air from being unable to be discharged through the air outlet 311 due to excessive air pressure in the duct 1, and also increasing the rate of cooling air discharge.

[0053] Further, refer to Figure 4 As shown, the cooling circulation mechanism also includes a centrifugal airflow channel 333. The rotor 33 includes a rotor disk 331 and a magnet 332 arranged on the rotor disk. The centrifugal airflow channel 333 is arranged on the side of the rotor disk 331 facing the stator 32, and includes a plurality of radial grooves arranged radially. There are multiple magnets 332, and the multiple magnets 332 are arranged corresponding to the coil winding 322 and arranged at intervals along the circumference of the rotor disk 331. The radial grooves are arranged in the gap between two adjacent magnets 332. By setting up the centrifugal airflow channel 333, the centrifugal force generated when the rotor 33 rotates at high speed can be used to automatically form a directional airflow channel. Forced convection heat dissipation can be achieved without the need for an additional power device, which is beneficial to reducing the volume and structural complexity of the cooling structure and achieving a lightweight design of the motor. In addition, by adopting the above structure, the cooling air can be accelerated to be discharged from the air outlet 311 on the motor housing 31, thereby improving the cooling efficiency.

[0054] Continue to refer to Figure 4As shown, preferably, the radial groove includes interconnected straight segments 3331 and curved segments 3332. The radial curved segments 3332 are arranged along the edge of the rotor disk 331. In the above solution, when the cooling airflow passes through the curved segments 3332, centrifugal force generates a circulation perpendicular to the main flow direction, breaking the laminar boundary layer and enhancing the heat exchange intensity between the cooling airflow and the surface of the magnet 332. The straight segments 3331 can avoid excessive turbulent energy loss caused by a purely curved spiral structure. In other words, the segmented flow channel design not only maintains the stability of the directional flow, but also enhances heat dissipation through local spiral disturbances, thereby enhancing the turbulence effect and heat dissipation efficiency. At the same time, since the straight section 3331 extends radially along the rotor disk 331, it can ensure that the cooling airflow can evenly cover the rotor disk 331, avoiding local overheating. The straight section 3331 can reduce the pressure head loss caused by continuous turning of the pure curved spiral flow channel, and the curved section 3332 assists in propelling the fluid through centrifugal force. The combination of the two reduces the total pressure drop by 15%-20% compared with a single curved spiral structure. Under high-speed conditions, the centrifugal force of the curved section 3332 dominates the flow acceleration, and at low speeds, the straight section 3331 maintains the basic flow rate, ensuring cooling stability under all operating conditions.

[0055] Further, refer to Figure 2 As shown, the aforementioned motor housing 31 includes an end cover, and the stator adjustment mechanism includes a drive member and a transmission member. The transmission member is respectively connected to the drive member, the mounting plate 321, and the cooling jacket 41. The drive member drives the mounting plate 321 and the cooling jacket 41 to move axially through the transmission member to adjust the size of the air gap 34 between the stator 32 and the rotor 33. Preferably, the drive member is a micro-motor 51 connected to the end cover of the motor housing 31. The transmission member includes a screw 521 that cooperates with the micro-motor 51 and a connecting seat 522 disposed on the screw 521 and connected to the mounting plate 321 and / or the cooling jacket 41. In the above solution, the micro-motor 51 has high precision and fast response, and can accurately control the adjustment distance of the stator 32 in conjunction with the screw 521 transmission mechanism. In addition, the micro-motor 51 is small in size and light in weight and can be directly disposed on the end cover of the motor housing 31, facilitating installation and commissioning.

[0056] Further, refer to Figure 1 and Figure 2As shown, the motor vibration damping mechanism also includes a vibration damping connecting arm and a buffer layer 312 arranged on the inner wall of the motor housing 31, and the two ends of the vibration damping connecting arm are respectively connected to the shell of the duct 1 and the motor housing 31. Preferably, the buffer layer 312 uses a rubber shock-absorbing pad with high damping characteristics to isolate the vibration inside the motor. The vibration damping connecting frame 11 is made of carbon fiber composite material and the vibration damping connecting frame 11 is also provided with a buffer pad at the connection with the duct 1 and the motor housing 31 to absorb vibration and dampen vibration. The use of carbon fiber composite material is also conducive to the lightweight design of the vibration damping connecting frame 11. In the above scheme, the provision of the vibration damping layer and the vibration damping connecting arm can further reduce the vibration transmitted from the motor to the duct 1 and even other parts of the propulsion device, which is conducive to ensuring the structural stability of the aircraft propulsion device.

[0057] Further, refer to Figure 1 As shown, in order to further improve the overall heat dissipation capacity of the aircraft propulsion device in this application, the aircraft propulsion device in this application is also provided with a ducted cooling mechanism. Figure 1 As shown, the ducted cooling structure includes a liquid cooling device 61 and a ducted cooling passage disposed inside the shell of the duct 1. The ducted cooling passage extends and is distributed inside the shell of the duct 1. At the same time, a connecting passage 62 is disposed inside the damping connecting arm 11. The ducted cooling passage and the connecting passage 62 are both connected to the liquid cooling device, and the connecting passage 62 is connected to the first circulation passage 411 in the cooling circulation mechanism. In the above scheme, the ducted cooling mechanism is organically combined with the motor cooling mechanism through the connecting passage. The ducted cooling mechanism can improve the heat dissipation capacity inside the duct 1, thereby providing a better heat dissipation environment for the aviation drive motor 3, and further improving the cooling efficiency of the motor cooling mechanism in this application, thereby improving the working efficiency, operational stability, and safety of the aviation drive motor 3 and the entire flight propulsion device in this application.

[0058] Reference Figure 6 As shown, as a preferred embodiment of the present invention, the aircraft propulsion device of the present invention further includes a monitoring unit 7 and a control unit 8. The monitoring unit 7 includes a temperature monitoring element for monitoring the temperature of the coil winding 322 and a distance monitoring element for monitoring the size of the air gap 34. The control unit 8 is respectively connected to the monitoring unit 7, the liquid cooling device 61, and the stator adjustment mechanism. The provision of the monitoring unit 7 enables real-time monitoring of the motor temperature and the distance between the stator 32 and the rotor 33. In conjunction with the control unit 8, the operating state of the cooling unit and the stator adjustment mechanism can be adjusted in a timely and accurate manner to maintain the entire aircraft propulsion device in optimal operating condition, ensure the stability of the aircraft propulsion device, and thus facilitate the flight safety of the aircraft.

[0059] The present application also provides an aircraft comprising a fuselage, wings, landing gear, and a power system, wherein the power system comprises at least two propulsion units symmetrically disposed on either side of the fuselage or on the wings on either side of the fuselage, each of the propulsion units comprising at least one aircraft propulsion device as described above. The use of the above-described propulsion device effectively meets the aircraft's higher requirements for power device efficiency, weight, and volume, thereby contributing to the development of high-performance, low-energy aircraft.

[0060] Anything not described in this application can be achieved by adopting or drawing on existing technologies.

[0061] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on the differences from other embodiments.

[0062] The foregoing is merely an embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various changes and variations. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present application should all be included within the scope of the claims of the present application.

Claims

1. An aviation drive motor is provided in an aircraft propulsion device, wherein the aircraft propulsion device comprises a power mechanism and the aviation drive motor, wherein the aviation drive motor is connected to the power mechanism to provide power to the power mechanism, and wherein: The aviation drive motor includes a motor cooling mechanism, which includes a motor housing and a cooling circulation mechanism disposed between a stator and a rotor of the aviation drive motor. The stator includes a mounting disk and a plurality of coil windings disposed on the mounting disk. The plurality of coil windings are arranged at intervals along the circumference of the mounting disk. The cooling circulation mechanism is disposed in gaps between the plurality of coil windings and / or in an air gap between the stator and the rotor, and the cooling circulation mechanism is connected to the motor housing. The motor vibration damping mechanism also includes a stator adjustment mechanism connected to the stator, and the stator adjustment mechanism drives the stator to move axially to adjust the axial distance between the stator and the rotor. The cooling circulation mechanism includes a cooling jacket and circulation blades connected to the cooling jacket, the circulation blades are arranged around the circumference of the cooling jacket and are arranged corresponding to the gaps between two adjacent coil windings, a first circulation passage for coolant flow is provided inside the cooling jacket, a second circulation passage for coolant flow is provided inside the circulation blades, the second circulation passage is connected to the first circulation passage, and the motor housing is further provided with an external circulation passage; A plurality of mounting grooves are provided on the side of the mounting disk facing the stator, a cooling jacket mounting seat is provided in the middle of the mounting disk in the radial direction, the cooling jacket is arranged in the mounting seat, a plurality of the coil windings are correspondingly arranged in the mounting grooves, and an air hole is provided between two adjacent mounting grooves, which penetrates the mounting disk in the axial direction, the air hole extends in the radial direction of the mounting disk and the width of the air hole is greater than the thickness of the circulation blade, the cooling circulation mechanism also includes a forced cooling fan provided on the side of the mounting disk away from the rotor, the cooling air blown out by the forced cooling fan enters the air gap through the air hole and both sides of the circulation blade.

2. The aviation drive motor according to claim 1, wherein: The cooling circulation mechanism also includes a centrifugal air flow channel. The rotor includes a rotor disk and a magnet arranged on the rotor disk. The centrifugal air flow channel is arranged on the side of the rotor disk facing the stator, and includes a plurality of radial grooves arranged radially. There are multiple magnets, and the multiple magnets are arranged corresponding to the coil windings and arranged at intervals along the circumference of the rotor disk. The radial groove is arranged in the gap between two adjacent magnets.

3. The aviation drive motor according to claim 2, wherein: The radial groove includes a straight section and a curved section that are connected to each other. The curved section is provided at an edge portion of the rotor disk along a radial direction of the rotor disk.

4. The aviation drive motor according to claim 1, wherein: The motor housing is also provided with an air outlet corresponding to the air gap, the air outlet is connected to the air gap and the air duct of the aircraft propulsion device, and one end of the air outlet connected to the air duct opens along the extension direction of the air duct toward the airflow outlet of the air duct.

5. The aviation drive motor according to claim 1, wherein: The motor housing includes an end cover, and the stator adjustment mechanism includes a driving member and a transmission member, the transmission member is respectively connected to the driving member, the mounting plate and the cooling jacket, and the driving member drives the mounting plate and the cooling jacket to move axially through the transmission member to adjust the size of the air gap between the stator and the rotor.

6. An aircraft propulsion device, characterized in that: It includes a duct, a power mechanism arranged inside the duct, and at least one aviation drive motor as described in any one of claims 1 to 5, the power mechanism is a ducted fan propeller, and the aviation drive motor is connected to the ducted fan propeller to provide power for the ducted fan propeller.

7. The aircraft propulsion device according to claim 6, characterized in that: It also includes a ducted cooling mechanism, the ducted cooling structure includes a liquid cooling device and a ducted cooling passage arranged inside the shell of the duct, a connecting passage is provided between the motor housing and the shell of the duct, the ducted cooling passage and the connecting passage are both connected to the liquid cooling device, and the connecting passage is connected to the cooling circulation mechanism.

8. An aircraft, characterized in that: It comprises a fuselage, wings, landing gear and a power system, wherein the power system comprises at least two groups of propulsion units symmetrically arranged on both sides of the fuselage or on the wings on both sides of the fuselage, and each of the propulsion units comprises at least one aircraft propulsion device as described in claim 7.

Images