An electric drive system and a flying device

Abstract

The application provides an electric driving system and a flight device, and relates to the technical field of electric driving. The electric driving system comprises an inner stator assembly and an outer rotor assembly; the inner stator assembly comprises an electric control mechanism and a stator shaft mechanism, the outer rotor assembly comprises a rotor mechanism, the electric control mechanism is arranged at one end of the stator shaft mechanism, the stator shaft mechanism is matched and installed with the electric control mechanism, and the rotor mechanism is sleeved on the outer side of the stator shaft mechanism; the electric control mechanism comprises a plurality of inversion units, and the plurality of inversion units are arranged in parallel in sectors at the end position of the stator shaft mechanism. The electric driving system can realize the technical effects of compact structure, high power density and high system reliability.

Description

Technical Field

[0001] This application relates to the field of electric drive technology, and more specifically, to an electric drive system and flight device. Background Technology

[0002] Currently, the low-altitude economy has become a hot topic in the industry, with electric vertical takeoff and landing (EVTOL) aircraft or flying cars, primarily driven by electrification, becoming the main research direction. Regarding electric drive systems, the future technological trends are high power, miniaturization, high power density, and high safety. However, existing applications of power drive systems in aircraft or flying cars, such as dual-motor systems suitable for coaxial dual-propeller arrangements, suffer from complex structures, and the advantages of miniaturization and lightweighting are not significant. Other types of electric drive systems suffer from problems such as non-compact structures, low power density, and low system reliability. Utility Model Content

[0003] The purpose of this application is to provide an electric drive system and flight device that can achieve the technical effects of compact structure, high power density and high system reliability.

[0004] In a first aspect, this application provides an electric drive system, including an inner stator assembly and an outer rotor assembly;

[0005] The inner stator assembly includes an electrical control mechanism and a stator shaft mechanism, and the outer rotor assembly includes a rotor mechanism. The electrical control mechanism is disposed at one end of the stator shaft mechanism, and the stator shaft mechanism is matched and installed with the electrical control mechanism. The rotor mechanism is sleeved on the outside of the stator shaft mechanism. The electrical control mechanism includes multiple inverter units, which are arranged in parallel in sectors at the end positions of the stator shaft mechanism.

[0006] In the above implementation process, the electric drive system adopts a single motor assembly with an inner stator assembly and an outer rotor assembly as the main structure. The inverter unit is integrated with the stator shaft mechanism, which is compact, facilitates heat dissipation design, and has high power density. Moreover, the electric drive system adopts sector-based drive control, which is conducive to increasing motor torque, improving redundancy and safety, and enhancing system reliability. Thus, the electric drive system can achieve the technical effects of compact structure, high power density, and high system reliability.

[0007] Furthermore, the electric drive system also includes a heat dissipation mechanism, which is installed between the electric control mechanism and the stator shaft mechanism, and the heat dissipation mechanism is matched with the electric control mechanism.

[0008] In the above implementation process, by setting a heat dissipation mechanism at the end of the stator shaft mechanism, the inverter power module is centrally cooled, which effectively improves the heat dissipation efficiency of the electronic control mechanism and the stator shaft mechanism, thereby increasing the power density of the electric drive system.

[0009] Furthermore, the heat dissipation mechanism includes a heat sink, which is attached to the electronic control mechanism.

[0010] In the above implementation process, by attaching the heat sink to the electronic control mechanism, the heat generated by the electronic control mechanism can be better conducted to the heat sink. That is, the heat sink can effectively increase the contact area between the heat-generating element and the air, accelerate the heat transfer, and then dissipate heat through the heat sink, thereby improving the heat dissipation effect.

[0011] Furthermore, the electric drive system also includes multiple motor windings, which are disposed on the stator shaft mechanism, and the inverter unit is connected to the corresponding motor winding.

[0012] In the above implementation process, multiple inverter units and distributed motor windings are connected to form the basic structure of the electric drive system. The three-phase output of the inverter unit is connected to the corresponding motor winding. Each inverter unit performs motor inverter control and outputs three-phase AC to the motor winding to realize motor drive.

[0013] Furthermore, the electric drive system also includes a high-voltage bus, the three-phase output of the inverter unit is connected to the corresponding motor windings, and the DC input of the inverter unit is connected to the high-voltage bus.

[0014] In the above implementation process, the DC input of the inverter unit is connected to the high voltage bus, and the DC high voltage is input to each inverter unit by the high voltage bus 130, so that each inverter unit performs motor inverter control and outputs three-phase AC to the motor windings to realize motor drive.

[0015] Furthermore, the inverter unit is a wide bandgap semiconductor module.

[0016] In the above implementation process, the power module of the inverter unit adopts a wide bandgap semiconductor module, which can take advantage of the high voltage resistance, high frequency and small size characteristics of the wide bandgap semiconductor module to achieve a compact device structure, modular design and centralized heat dissipation.

[0017] Furthermore, the inverter unit includes multiple wide-bandgap semiconductor power transistors and an input capacitor, and the multiple wide-bandgap semiconductor power transistors and the input capacitor are connected in a full-bridge circuit configuration.

[0018] In the above implementation process, by utilizing the characteristics of wide bandgap semiconductor power transistors such as high voltage resistance, high frequency, and small size, the inverter unit is designed as a full-bridge module, which can achieve compact device structure, modular design, and centralized heat dissipation.

[0019] Furthermore, the outer rotor assembly also includes a propeller mechanism disposed outside the rotor mechanism.

[0020] In the above implementation process, the rotor mechanism and propeller mechanism are integrated into one unit, resulting in a higher degree of structural integration. Moreover, the direct drive method eliminates the need for a speed reduction device, greatly simplifying the system structure and bringing significant benefits to miniaturization and lightweight applications.

[0021] Furthermore, the propeller mechanism includes multiple propellers, which are respectively arranged on the outside of the rotor mechanism at a preset angle.

[0022] In the above implementation process, multiple propellers are respectively arranged on the outside of the rotor mechanism at a preset angle, so as to provide the airflow required for flight when the propellers rotate.

[0023] Secondly, this application provides a flight device including the electric drive system described in any of the first aspects.

[0024] Other features and advantages disclosed in this application will be set forth in the following description, or some features and advantages may be inferred from the description or determined without doubt, or may be learned by practicing the above-described technology disclosed in this application.

[0025] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the structure of the electric drive system provided in the embodiments of this application;

[0028] Figure 2 This is another schematic diagram of the electric drive system provided in an embodiment of this application;

[0029] Figure 3 This is a schematic diagram of the structure of the inverter unit and motor winding provided in the embodiments of this application;

[0030] Figure 4 The circuit structure diagram of the inverter unit provided in the embodiment of this application is shown. Detailed Implementation

[0031] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely represents selected embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0032] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0033] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0034] Furthermore, the terms "installation," "setup," "equipped with," "connection," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; they can refer to a mechanical connection or a point connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0035] Furthermore, the terms "first," "second," etc., are primarily used to distinguish different devices, components, or parts (which may be the same or different in specific type and construction), and are not intended to indicate or imply the relative importance or quantity of the indicated devices, components, or parts. Unless otherwise stated, "a plurality of" means two or more.

[0036] Generally, the low-altitude economy has become a hot topic in the industry, with electric vertical takeoff and landing (EVTOL) aircraft or flying cars, primarily powered by electrification, becoming the main research direction. Examples of commonly used technical approaches regarding the application of power drive systems in aircraft or flying cars are as follows:

[0037] ① An electric motor assembly and flight equipment, including a housing assembly, an electric motor, a reduction gear, a control device and a cooling device, adopting a single motor integration and a unified cooling device to achieve heat dissipation of the assembly;

[0038] ② A transmission system, a hybrid drive assembly, and a flying car, comprising an engine, dual motors, a transmission, and a clutch, is actually an integrated drive system applied to a flying car;

[0039] ③ An electric motor and flight equipment, including a stator, a rotor and a heat dissipation device, wherein the external rotor motor is equipped with multiple cooling fans, which can dissipate heat individually according to the heat dissipation needs of different areas of the motor, thereby improving heat dissipation efficiency;

[0040] ④ A powertrain and vehicle, comprising dual motors, dual electronic controls and a coaxial mechanism, achieving a coaxial dual-propeller arrangement, high structural integration, conducive to lightweight and miniaturized layout, and high redundancy;

[0041] ⑤ A hub motor for an electric flying car, comprising a hub motor, an inner splined bushing, planetary gears and a housing, wherein different power outputs and high / low speed switching are adjusted by a gear shifting fork device to realize multiple working states of the flying car.

[0042] The architectures ① and ② above are widely used in the field of new energy vehicles, are relatively conventional, and have limited innovation; ③ and ⑤ are both applications of hub motors as distributed drives, which emphasize innovation in heat dissipation and execution structure; ④ adopts a dual-motor system, which is particularly suitable for coaxial dual-propeller arrangement, but the structure is complex and the advantages brought by small size and lightweight are not significant.

[0043] To address the aforementioned technical problems, this application provides an electric drive system applicable to flight devices (such as electric vertical takeoff and landing aircraft or flying cars). This electric drive system employs a single-motor assembly with an inner stator assembly and an outer rotor assembly as its main structure. The inverter unit is integrated with the stator shaft mechanism, resulting in a compact structure, convenient heat dissipation design, and high power density. Furthermore, the electric drive system utilizes sector-based drive control, which increases motor torque, enhances redundancy and safety, and improves system reliability. Therefore, this electric drive system achieves the technical advantages of a compact structure, high power density, and high system reliability.

[0044] Please see Figures 1 to 3 , Figure 1 This is a schematic diagram of the structure of the electric drive system provided in the embodiments of this application. Figure 2 This is another structural schematic diagram of the electric drive system provided in an embodiment of this application. Figure 3 This is a schematic diagram of the inverter unit and motor winding provided in an embodiment of this application; the electric drive system includes an inner stator assembly and an outer rotor assembly;

[0045] The inner stator assembly includes an electrical control mechanism 100 and a stator shaft mechanism 200, and the outer rotor assembly includes a rotor mechanism 300. The electrical control mechanism 100 is disposed at one end of the stator shaft mechanism 200, and the stator shaft mechanism 200 is matched and installed with the electrical control mechanism 100. The rotor mechanism 300 is sleeved on the outside of the stator shaft mechanism 200. The electrical control mechanism 100 includes multiple inverter units 111~116 (inverter unit 111, inverter unit 112, inverter unit 113, inverter unit 114, inverter unit 115, inverter unit 116), and the multiple inverter units are arranged in parallel in sectors at the end position of the stator shaft mechanism 200.

[0046] For example, the stator shaft mechanism 200 is an inner stator (internal fixed portion); the stator shaft mechanism 200 includes:

[0047] Stator core: Made of laminated magnetic silicon steel sheets, with slots on the surface to accommodate the stator windings. The slot design directly affects the insulation and heat dissipation efficiency of the windings; for example, semi-closed slots are suitable for low-voltage motors, while open slots are used in high-voltage applications.

[0048] Stator windings: typically made of high-strength enameled copper or aluminum wire, distributed in three phases and connected in a star or delta configuration to form a rotating magnetic field;

[0049] Frame and bracket: The frame fixes the stator core and supports the rotor through the end cover; in external rotor motors, the stator bracket needs to bear the weight of the main shaft and the external rotor. For example, the stator bracket and main shaft flange of wind turbine generators need to be designed with high strength.

[0050] For example, the rotor mechanism 300 is an outer rotor (external rotating portion); the rotor mechanism 300 includes:

[0051] Rotor yoke: It is barrel-shaped and made of magnetic material. A permanent magnet (such as neodymium iron boron magnet) is fixed on the inner circumference and connected to the main shaft through the rotor bushing.

[0052] Magnetic pole layout: Large external rotor motors (such as direct-drive wind turbines) are usually designed with 30-40 pairs of magnetic poles. The magnetic pole fixing method is more stable due to the low centrifugal force.

[0053] Shaft and bearings: The outer rotor bushing needs to bear the load of the entire wind turbine or impeller, and usually uses double large bearings to support it to ensure smooth rotation.

[0054] For example, when current flows through the three-phase windings of the inner stator, a rotating magnetic field is generated. The permanent magnet magnetic field of the outer rotor interacts with the stator magnetic field, driving the outer rotor to rotate. Since the outer rotor surrounds the stator, its magnetic field coverage area is larger, which is beneficial for high torque output; the outer rotor structure dissipates heat through a large surface area, and heat is directly transferred to the external environment, making it suitable for high-power scenarios (such as electric vehicle drives); at the same time, the rotor has a large inertia, requiring a balanced design to reduce vibration and noise.

[0055] For example, the inverter unit in the electronic control mechanism 100 can be a full-bridge, half-bridge / push-pull topology, multi-level topology, etc., which are only examples and not limitations. It should be noted that the structure of the inverter unit can be selected according to actual needs and is not limited to the structures mentioned above; wherein:

[0056] Full-bridge inverter unit: It consists of a bridge structure composed of 4 switching devices (such as IGBT and MOSFET), which generate alternating voltage by alternating conduction, supporting high-power scenarios (such as photovoltaic inverters).

[0057] Half-bridge / push-pull topology: suitable for low to medium power applications, with lower cost but slightly lower efficiency;

[0058] Multilevel topology: Reduces harmonics through layered voltage output, suitable for high-voltage, high-power scenarios (such as grid-scale energy storage).

[0059] The electric drive system provided in this application embodiment adopts a single motor assembly with an inner stator assembly and an outer rotor assembly as the main structure. The inverter unit is integrated with the stator shaft mechanism, which is compact, facilitates heat dissipation design, and has high power density. Moreover, the electric drive system adopts sector-based drive control, which is beneficial to increase motor torque, improve redundancy and safety, and enhance system reliability. Thus, the electric drive system can achieve the technical effects of compact structure, high power density, and high system reliability.

[0060] In some embodiments, the electric drive system further includes a heat dissipation mechanism 120, which is installed between the electric control mechanism 100 and the stator shaft mechanism 200, and the heat dissipation mechanism 120 is matched with the electric control mechanism 100.

[0061] For example, by providing a heat dissipation mechanism 120 at the end of the stator shaft mechanism 200, the inverter power module is centrally cooled, which effectively improves the heat dissipation efficiency of the electronic control mechanism 100 and the stator shaft mechanism 200, thereby increasing the power density of the electric drive system.

[0062] In some embodiments, the heat dissipation mechanism 120 includes a heat sink, which is attached to the electronic control mechanism 100.

[0063] For example, by attaching a heat sink to the electronic control mechanism 100, the heat generated by the electronic control mechanism 100 can be better conducted to the heat sink. That is, the heat sink can effectively increase the contact area between the heat-generating element and the air, accelerate heat transfer, and then dissipate heat through the heat sink, thereby improving the heat dissipation effect.

[0064] For example, the material of the heat sink can be:

[0065] Copper: It has the best thermal conductivity (thermal conductivity of about 401 W / (m·K)), but it is expensive, heavy, and easily oxidized. It is mostly used in high-end applications (such as GPU heatsinks).

[0066] Aluminum has about 50% of the thermal conductivity of copper (thermal conductivity of about 237 W / (m·K)), but it is lightweight, low in cost and easy to process, making it the mainstream choice (such as CPU heatsinks).

[0067] Composite materials: Copper-aluminum combined design balances thermal conductivity and lightweight, such as aluminum-based copper-embedded plates or copper-aluminum welded structures, suitable for scenarios that balance performance and cost.

[0068] New materials such as graphite sheets (lightweight and highly thermally conductive) and ceramics (alumina and aluminum nitride, which have both thermal conductivity and insulation properties) are gradually being applied in the fields of power electronics and LEDs.

[0069] It should be noted that the material of the heat sink can be selected according to actual needs, and is not limited to the materials mentioned above.

[0070] In some embodiments, the electric drive system further includes a plurality of motor windings 211 to 216 (motor winding 211, motor winding 212, motor winding 213, motor winding 214, motor winding 215, and motor winding 216), the plurality of motor windings being disposed on the stator shaft mechanism, and the inverter unit being connected to the corresponding motor winding.

[0071] For example, multiple inverter units and distributed motor windings are connected to form the basic structure of an electric drive system. The three-phase output of the inverter unit is connected to the corresponding motor winding. Each inverter unit performs motor inverter control and outputs three-phase AC to the motor winding to realize motor drive.

[0072] In some embodiments, the electric drive system further includes a high-voltage bus 130, the three-phase output of the inverter unit is connected to the corresponding motor windings, and the DC input of the inverter unit is connected to the high-voltage bus 130.

[0073] For example, the DC input of the inverter unit is connected to the high-voltage bus 130, and the DC high voltage is input to each inverter unit through the high-voltage bus 130, so that each inverter unit performs motor inverter control and outputs three-phase AC to the motor windings to realize motor drive.

[0074] In some embodiments, the inverter unit is a wide bandgap semiconductor module.

[0075] For example, the power module of the inverter unit adopts a wide bandgap semiconductor module, which can take advantage of the high voltage resistance, high frequency and small size of the wide bandgap semiconductor module to achieve a compact device structure, modular design and centralized heat dissipation.

[0076] For example, the wide bandgap semiconductor module can be gallium nitride (GaN), silicon carbide (SiC), etc., which are only examples and not limitations. It should be noted that the wide bandgap semiconductor module can use other materials as needed, and is not limited to gallium nitride (GaN) and silicon carbide (SiC) mentioned above.

[0077] Please see Figure 4 , Figure 4 The circuit structure diagram of the inverter unit provided in the embodiment of this application is shown.

[0078] In some embodiments, the inverter unit includes a plurality of wide-bandgap semiconductor power transistors and an input capacitor, which are connected in a full-bridge circuit configuration.

[0079] For example, by utilizing the high voltage resistance, high frequency, and small size characteristics of wide bandgap semiconductor power transistors, the inverter unit can be designed as a full-bridge module, which can achieve compact device structure, modular design, and centralized heat dissipation.

[0080] For example, the inverter unit power module adopts a wide bandgap semiconductor (SiC / GaN) module. Taking advantage of its high voltage resistance, high frequency, and small size, it is designed as a full-bridge module, as shown in Figure 4. Taking one group as an example (111), it includes six groups of power transistors (a~f) and an input capacitor 121. The sources of the upper power transistors a / c / e are connected to the drains of the lower power transistors b / d / f, and are respectively connected to the three-phase windings. The drains of the upper power transistors a / c / e are connected together and connected to the positive terminal of the input capacitor 121. The sources of the lower power transistors b / d / f are connected together and connected to the negative terminal of the input capacitor 121. The power transistors are preferably SiC-MOSFET modules or GaN modules. Since the power level of each inverter unit is a fraction of the total power, a single power transistor can be used. In particular, GaN power transistors, with their small power (~10kW level) and planar packaging technology, can achieve compact device structure, modular design, and centralized heat dissipation.

[0081] In some embodiments, the outer rotor assembly further includes a propeller mechanism 400 disposed outside the rotor mechanism 300.

[0082] For example, the rotor mechanism 300 and the propeller mechanism 400 are integrated into one unit, resulting in a higher degree of structural integration. Moreover, the direct drive method eliminates the need for a speed reduction device, greatly simplifying the system structure and bringing significant benefits to miniaturization and lightweight applications.

[0083] In some embodiments, the propeller mechanism 400 includes a plurality of propellers, which are respectively arranged on the outside of the rotor mechanism at a preset angle.

[0084] For example, multiple propellers are respectively arranged at a preset angle on the outside of the rotor mechanism, thereby providing the airflow required for flight when the propellers rotate.

[0085] In some embodiments, this application provides a flight device, including Figures 1 to 4 The electric drive system shown; for example, the flight device may be an electric vertical take-off and landing aircraft or a flying car, etc., which are only examples and not limitations.

[0086] For example, combined Figures 1 to 4 As shown, the electric drive system provided in this application embodiment has the following technical features:

[0087] 1. The electronically controlled inverter unit is integrated with the stator and located at the end position, which is compact and conducive to miniaturization design;

[0088] 2. The inverter unit power level is reduced, the device selection is simpler, and it is easy to modularize and miniaturize. Wide bandgap semiconductor (SiC / GaN) power modules are preferred to increase the frequency and reduce the loss.

[0089] 3. The external rotor and propeller are integrated into one unit, with direct drive control, eliminating the need for a reduction gear and simplifying the structure;

[0090] 4. The segmented winding sector drive control increases the motor torque and enables redundant system control, resulting in high robustness and improved system reliability.

[0091] This electric drive system employs a distributed electric drive technology, using a single motor assembly with an inner stator and an outer rotor structure, resulting in a simple and compact structure. The electronic control unit is integrated with the inner stator, and the outer rotor housing is integrated with the propeller, resulting in higher structural integration. Moreover, the direct drive method eliminates the need for a reduction gear, greatly simplifying the system structure and significantly improving miniaturization and lightweight applications. In addition, the embodiments of this application employ a flexible split-winding design and sector-based control, resulting in higher control redundancy and stronger robustness and reliability.

[0092] It should be understood that the phrases "in this embodiment," "in this application embodiment," or "as an optional implementation" throughout the specification mean that a specific feature, structure, or characteristic related to an embodiment is included in at least one embodiment of this application. Therefore, the phrases "in this embodiment," "in this application embodiment," or "as an optional implementation" appearing throughout the specification do not necessarily refer to the same embodiment. Furthermore, these specific features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Those skilled in the art should also understand that the embodiments described in the specification are all optional embodiments, and the actions and modules involved are not necessarily essential to this application.

[0093] In the various embodiments of this application, it should be understood that the sequence number of each process does not necessarily imply the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of this application.

[0094] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of protection of the claims.

Claims

1. An electric drive system, characterized in that, Including the inner stator assembly and the outer rotor assembly; The inner stator assembly includes an electrical control mechanism and a stator shaft mechanism, and the outer rotor assembly includes a rotor mechanism. The electrical control mechanism is disposed at one end of the stator shaft mechanism, and the stator shaft mechanism is matched and installed with the electrical control mechanism. The rotor mechanism is sleeved on the outside of the stator shaft mechanism. The electrical control mechanism includes multiple inverter units, which are arranged in parallel in sectors at the end positions of the stator shaft mechanism.

2. The electric drive system according to claim 1, characterized in that, The electric drive system further includes a heat dissipation mechanism, which is installed between the electric control mechanism and the stator shaft mechanism, and the heat dissipation mechanism is matched with the electric control mechanism.

3. The electric drive system according to claim 2, characterized in that, The heat dissipation mechanism includes a heat sink, which is attached to the electronic control mechanism.

4. The electric drive system according to claim 1, characterized in that, The electric drive system also includes multiple motor windings, which are disposed on the stator shaft mechanism, and the inverter unit is connected to the corresponding motor winding.

5. The electric drive system according to claim 4, characterized in that, The electric drive system also includes a high-voltage bus, the three-phase output of the inverter unit is connected to the corresponding motor windings, and the DC input of the inverter unit is connected to the high-voltage bus.

6. The electric drive system according to claim 1, characterized in that, The inverter unit is a wide bandgap semiconductor module.

7. The electric drive system according to claim 6, characterized in that, The inverter unit includes multiple wide-bandgap semiconductor power transistors and an input capacitor, which are connected in a full-bridge circuit configuration.

8. The electric drive system according to claim 1, characterized in that, The outer rotor assembly also includes a propeller mechanism disposed outside the rotor mechanism.

9. The electric drive system according to claim 8, characterized in that, The propeller mechanism includes multiple propellers, which are respectively arranged on the outside of the rotor mechanism at a preset angle.

10. A flight device, characterized in that, Includes the electric drive system according to any one of claims 1 to 9.

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