Brushless motor for eVTOL, power control system and eVTOL

Abstract

The invention relates to the technical field of eVTOLs, in particular to a brushless motor for an eVTOL, a power control system and the eVTOL. The brushless motor provided by the invention at least comprises a rotor module which can be selectively arranged on the inner side or the outer side of a stator module so as to adapt to different requirements of eVTOL for motor parameters in different flight scenes; the stator module is arranged corresponding to the rotor module and at least comprises a stator iron core, a winding and a machine base, the stator iron core is wound with the winding, and the machine base is used for fixing the stator iron core and adapting to structures and heat dissipation requirements of eVTOL in different flight scenes; and the magnetic pole detection device is configured on the side surface of the winding and is used for outputting a magnetic pole detection signal according to the alternating magnetic flux of the winding and cooperatively realizing detection and control on the running state of the motor. The eVTOL full flight scene can be covered, and core technical support is provided for practicability of the fields of urban air traffic, emergency rescue and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of eVTOL (Electronic Vertical Transmission Vehicle), and more particularly, to a brushless motor, a power control system, and an eVTOL for use in an eVTOL. Background Art

[0002] eVTOLs (electric vertical take-off and landing) are a new type of aircraft powered by electricity, capable of vertical take-off and landing, as well as horizontal flight. They eliminate the need for traditional runways and can operate flexibly in complex environments, from densely populated urban areas to remote locations. They are considered a key component of future urban air mobility, emergency rescue, and logistics. Compared to traditional fuel-powered aircraft, eVTOLs offer significant advantages such as low noise, zero emissions, and ease of operation. However, they place extremely high demands on the powertrain's power density, reliability, lightweight design, and energy efficiency.

[0003] As the core component of the eVTOL power system, the brushless motor is an electric motor that uses an electronic controller instead of traditional brushes and commutators. It converts electrical energy into mechanical energy through the principle of electromagnetic induction, driving the propeller to generate thrust. It has the characteristics of high efficiency, long life, smooth operation, and low noise, and can accurately match the eVTOL's refined power output requirements.

[0004] In the propeller drive system of eVTOL, the performance of brushless motors directly determines the lift, endurance, controllability and safety redundancy of the aircraft. Although brushless motor technology is relatively mature, it still faces many challenges in eVTOL applications:

[0005] First, eVTOLs are highly sensitive to vehicle weight. Increasing motor power often relies on increasing winding turns and thickening magnets, which can easily lead to increased weight. However, excessive lightweighting can compromise performance and safety, necessitating an optimal balance between motor parameters and weight.

[0006] Secondly, heat dissipation and stability issues are significant under complex operating conditions. eVTOL flight scenarios are diverse, and motors must adapt to varying loads and ambient temperatures. Heat generated during high power output and reduced heat dissipation efficiency at high altitudes affect operational stability. Traditional heat dissipation designs are unable to meet these requirements, necessitating the integration of new heat dissipation designs while also avoiding excess weight.

[0007] Finally, different flight scenarios have very different requirements for motor size, strength, bearing performance, etc. Traditional specification motors are difficult to cover all scenarios, and core components such as rotors and stators need to be customized according to the application scenarios.

[0008] Therefore, there is an urgent need for a dedicated brushless motor suitable for eVTOL application scenarios. Summary of the Invention

[0009] The purpose of the present invention is to provide a brushless motor, power control system and eVTOL for eVTOL, so as to solve the problem that traditional brushless motors are difficult to adapt to the power requirements of eVTOL full flight scenarios.

[0010] To achieve the above objectives, the present invention provides a brushless motor for eVTOL, comprising at least:

[0011] The rotor module can be selectively arranged inside or outside the stator module to adapt to the differentiated motor parameter requirements of different eVTOL flight scenarios;

[0012] The stator module is arranged corresponding to the rotor module and includes at least a stator core, windings, and a base. The stator core is wound with windings, and the base is used to fix the stator core and adapt to the structural and heat dissipation requirements of different eVTOL flight scenarios;

[0013] The magnetic pole detection device is arranged on the side of the winding and is used to output a magnetic pole detection signal according to the alternating magnetic flux of the winding, so as to realize the detection and control of the operating state of the motor.

[0014] In some embodiments, the rotor module, located inside the stator module, includes:

[0015] The rotor core, composed of permanent magnets and iron, is located inside the stator module and is driven by the internal magnetic field.

[0016] The crankshaft is integrated with the permanent magnet and serves as the rotating axis;

[0017] The bearing is mounted on the crankshaft and is used to fix the crankshaft;

[0018] The stator module comprises:

[0019] The stator core is made of laminated silicon steel sheets;

[0020] The winding is made of multiple strands of fine copper wire;

[0021] The base serves as structural support and heat dissipation carrier.

[0022] In some embodiments, the magnet thickness of the rotor core is 0.4-0.8 mm and the circumferential width is 1.8-2.6 mm;

[0023] The crankshaft has a diameter of 2.5-4.5 mm and a length of 8-16 mm.

[0024] In some embodiments, the laminated silicon steel sheets of the stator core have a thickness of 0.3-0.4 mm and are coated with a resin coating of 0.05-0.09 mm;

[0025] The winding is made of 7-11 strands of copper wire, the diameter of the copper wire is 0.1-0.25 mm, and the number of turns is 25-45.

[0026] In some embodiments, the base is made of carbon fiber composite, aluminum alloy 7075, aluminum-based composite material, forged aluminum alloy or magnesium alloy.

[0027] In some embodiments, the bearing is a ceramic ball bearing, and the inner diameter is adapted to the crankshaft.

[0028] In some embodiments, the rotor module, located outside the stator module, includes:

[0029] The rotor core is composed of permanent magnets and iron, and is driven by the external magnetic field to achieve rotation;

[0030] The crankshaft is fixedly connected to the rotor core and is the rotating axis;

[0031] A bearing is provided between the circuit board and the crankshaft to support rotation;

[0032] The stator module comprises:

[0033] The stator core is made of laminated silicon steel sheets;

[0034] The winding is made of multiple strands of fine copper wire;

[0035] The base serves as structural support and heat dissipation carrier.

[0036] In some embodiments, the magnet thickness of the rotor core is 0.7-1.3 mm and the circumferential width is 2.2-3.1 mm;

[0037] The crankshaft has a diameter of 3.5-5.0 mm and a length of 11-17 mm.

[0038] In some embodiments, the stator core uses laminated silicon steel sheets with a thickness of 0.3-0.45 mm and a 0.05-0.1 mm resin coating;

[0039] The winding is made of 8-11 strands of copper wire, the diameter of the copper wire is 0.12-0.25 mm, and the number of turns is 28-40.

[0040] In some embodiments, the base is made of aluminum alloy-graphene composite, titanium alloy-aluminum alloy composite, carbon fiber-titanium alloy composite or high-temperature alloy material.

[0041] In some embodiments, the bearing is a magnetic bearing.

[0042] In some embodiments, the brushless motor further comprises a circuit board:

[0043] The circuit board is fixed to the non-rotating end of the machine base, receives the magnetic pole detection signal and outputs a PWM (pulse width modulation) waveform to the U / V / W phase winding.

[0044] In order to achieve the above object, the present invention provides a power control system based on a brushless motor, comprising:

[0045] Such as the brushless motors used for eVTOL mentioned above;

[0046] The fuselage circuit, including the fuselage controller, is used to manage the operating status of the entire machine;

[0047] a motor circuit, connected to the body circuit, comprising a motor controller and a three-phase drive circuit;

[0048] The motor controller is used to convert the instructions of the fuselage controller into motor control signals;

[0049] The three-phase drive circuit is connected to the U / V / W phases of the brushless motor.

[0050] In order to achieve the above object, the present invention provides a power control system based on a brushless motor, comprising:

[0051] Such as the brushless motors used for eVTOL mentioned above;

[0052] Body circuit, including body controller and motor controller:

[0053] The body controller is used to manage the operation status of the entire machine, and the motor controller is used to convert the instructions of the body controller into motor control signals;

[0054] The three-phase drive circuit is connected to the U / V / W phases of the brushless motor.

[0055] In some embodiments, there are multiple brushless motors, and the multiple brushless motors are distributed at different positions of the fuselage according to the flight scenario requirements of the eVTOL.

[0056] In some embodiments, the plurality of brushless motors are coordinated through a motor controller;

[0057] The motor controller dynamically matches the output combination of multiple brushless motors according to the power requirements of different eVTOL flight scenarios.

[0058] In some embodiments, the motor controller further includes a continuously variable speed control module, which uses a collaborative control algorithm of multiple brushless motors to achieve smooth speed control of the motor.

[0059] To achieve the above objectives, the present invention provides an eVTOL, comprising at least a fuselage, propellers, and a power control system based on a brushless motor as described above:

[0060] The power control system controls the brushless motor to provide flight power for the eVTOL.

[0061] The present invention provides a brushless motor, power control system and eVTOL for eVTOL, which solves the adaptability problem of single-specification motors through the modular layout of the motor's inner / outer rotors and scenario-based parameter customization; the power control system relies on a multi-motor collaborative algorithm to achieve precise control, safety redundancy and energy efficiency optimization, and can cover all flight scenarios, providing core technical support for practical application in urban air traffic, emergency rescue and other fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0062] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which like reference numerals denote like features throughout, wherein:

[0063] Figure 1a A front view of a brushless motor for eVTOL according to an embodiment of the present invention is disclosed;

[0064] Figure 1b A top view of a brushless motor for eVTOL according to one embodiment of the present invention is disclosed;

[0065] Figure 1c An axonometric diagram of a brushless motor for eVTOL according to one embodiment of the present invention is disclosed;

[0066] Figure 2a An exploded isometric view of a brushless motor for eVTOL according to an embodiment of the present invention is disclosed;

[0067] Figure 2b An exploded front view of a brushless motor for eVTOL according to an embodiment of the present invention is disclosed;

[0068] Figure 3a A front view of a stator module according to an embodiment of the present invention is disclosed;

[0069] Figure 3b An axonometric view of a stator module according to an embodiment of the present invention is disclosed;

[0070] Figure 4a A front view of a rotor module according to an embodiment of the present invention is disclosed;

[0071] Figure 4b An axonometric view of a rotor module according to an embodiment of the present invention is disclosed;

[0072] Figure 5a A front view of a brushless motor for eVTOL according to another embodiment of the present invention is disclosed;

[0073] Figure 5b A left side view of a brushless motor for eVTOL according to another embodiment of the present invention is disclosed;

[0074] Figure 5c A top view of a brushless motor for eVTOL according to another embodiment of the present invention is disclosed;

[0075] Figure 6a An exploded isometric view of a brushless motor for eVTOL according to another embodiment of the present invention is disclosed;

[0076] Figure 6b An axonometric diagram of a brushless motor for eVTOL according to another embodiment of the present invention is disclosed;

[0077] Figure 7a An axonometric view of a portion of an eVTOL structure according to an embodiment of the present invention is disclosed;

[0078] Figure 7b A top view of a partial structure of an eVTOL according to an embodiment of the present invention is disclosed.

[0079] The meanings of the reference numerals in the figures are as follows:

[0080] 110 stator module; 111 stator core; 112 winding; 113 machine base;

[0081] 120 rotor module; 121 crankshaft; 122 rotor core; 123 bearing;

[0082] 130 magnetic pole detection device;

[0083] 101 bracket; 102 circuit board; 103 lead wire;

[0084] 211 stator core; 212 winding;

[0085] 221 crankshaft; 222 rotor core; 223 bearing;

[0086] 230 magnetic pole detection device; 202 circuit board; 203 connector;

[0087] 31 fuselage; 32 propeller blades; 33 power control system. DETAILED DESCRIPTION

[0088] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present 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 only used to explain the invention and are not intended to limit the invention.

[0089] The brushless motor proposed in this invention for eVTOL meets the differentiated requirements of motor power, size, weight, and heat dissipation for different flight scenarios (such as ultra-compact integration, high-altitude cruising, heavy-load takeoff and landing, etc.). Through the coordinated layout of multiple brushless motors, the redundant safety and operating efficiency of the power system are improved, solving the problems of traditional specification motors being insufficiently adaptable to eVTOL and the difficulty in balancing weight and performance.

[0090] The present invention proposes a brushless motor for eVTOL, comprising at least:

[0091] The rotor module can be selectively arranged on the inner side or the outer side of the stator module;

[0092] The stator module is arranged corresponding to the rotor module, and comprises at least a stator core, a winding and a base, wherein the stator core is wound with the winding, and the base is used to fix the stator core;

[0093] The magnetic pole detection device is arranged on the side of the winding and is used to output a voltage according to the alternating magnetic flux of the winding.

[0094] Furthermore, the brushless motor further includes a circuit board:

[0095] The circuit board is fixed to the non-rotating end of the machine base, receives magnetic pole detection signals and outputs PWM waveforms to the U / V / W phase windings. By precisely controlling the winding current switching, it achieves fine adjustment of the motor speed and torque, ensuring the control stability of the eVTOL under complex working conditions.

[0096] The brushless motor proposed in this invention for eVTOL realizes the inner / outer layout scheme of the rotor module (hereinafter referred to as the inner rotor scheme and the outer rotor scheme) through modular design. It combines the coordinated optimization of the parameters of the stator module and the rotor module, such as the scenario-based matching of magnet size, silicon steel sheet specifications, winding parameters and base material, and the real-time magnetic flux feedback of the magnetic pole detection device, to form a power solution adapted to the full flight scenario of eVTOL.

[0097] The brushless motor for eVTOL proposed in the present invention adapts to the power requirements of different eVTOL flight scenarios by matching the parameters of the rotor module and the stator module.

[0098] First, combine Figures 1a to 4b The inner rotor solution of the brushless motor used in eVTOL is described in detail.

[0099] Figures 1a to 1c The front view, top view and isometric view of a brushless motor for eVTOL according to an embodiment of the present invention are disclosed. Figures 1a to 1c As shown, the present invention proposes a brushless motor for eVTOL, comprising at least:

[0100] The rotor module 120 is arranged inside the stator module 110;

[0101] The stator module 110 is arranged corresponding to the rotor module 120, and includes a stator core 111, a winding 112 and a base 113. The stator core 111 is wound with the winding 112, and the base is used to fix the bearing 123 and the stator core 111;

[0102] The magnetic pole detection device 130 is disposed on a side of the winding 112 and is used to output a voltage according to the alternating magnetic flux of the winding 112 .

[0103] Figure 2a and Figure 2b The following respectively discloses an exploded isometric view and an exploded front view of a brushless motor for eVTOL according to an embodiment of the present invention. Figure 3a and Figure 3b The main view and the axonometric view of the stator module according to an embodiment of the present invention are respectively disclosed. Figures 2a to 3b As shown, the stator module 110 includes:

[0104] The stator core 111 is made of laminated silicon steel sheets, and uses low iron loss materials to reduce electromagnetic losses;

[0105] The winding 112 is wound with multiple strands of fine copper wire to improve current carrying capacity and heat dissipation efficiency;

[0106] The base 113 serves as a structural support and heat dissipation carrier, taking into account both lightweight and functional adaptability.

[0107] In this embodiment, the laminated silicon steel sheets of the stator core have a thickness of 0.3-0.4 mm and are coated with a 0.05-0.09 mm resin coating. Differentiated selection of silicon steel sheet thickness can balance iron loss and structural strength, while the resin coating can achieve insulation, wear resistance, or heat dissipation enhancement (such as a coating design with heat dissipation microchannels) according to scenario requirements.

[0108] There are six windings 112 , each of which is wound with 7-11 strands of copper wire, the diameter of the copper wire is 0.1-0.25 mm, and the number of turns is 25-45. By optimizing the combination of the number of strands, wire diameter, and number of turns, a balance between power density and energy consumption control is achieved.

[0109] The base 113 is made of carbon fiber composite, aluminum alloy 7075, aluminum-based composite material, forged aluminum alloy or magnesium alloy, corresponding to the scene requirements of extreme lightweight, conventional lightweight, heat dissipation enhancement, high strength and lightweight + medium strength, achieving precise matching of structural performance and scene adaptation.

[0110] Figure 4a and Figure 4bThe front view and the axonometric view of the rotor module according to an embodiment of the present invention are respectively disclosed. Figure 2a to Figure 2b as well as Figures 4a to 4b As shown, the rotor module 120 includes:

[0111] The rotor core 122 is composed of permanent magnets and iron and is located inside the stator module 110. The rotor core 122 is driven by the magnetic field inside the stator module 110.

[0112] The crankshaft 121 is integrated with the permanent magnet and serves as a rotating shaft;

[0113] The bearing 123 is sleeved on the crankshaft 121 and is used to fix the crankshaft 121 .

[0114] In this embodiment, the magnet thickness of the rotor core 122 is 0.4-0.8 mm, the circumferential width is 1.8-2.6 mm, the diameter of the crankshaft is 2.5-4.5 mm, and the length is 8-16 mm. Through the gradient design of the magnet and crankshaft sizes, different power output requirements from low-load cruising to high-load take-off and landing can be matched.

[0115] The bearing 123 is a ceramic ball bearing, the inner diameter of which is adapted to the crankshaft 121 and the outer diameter of which matches the inner diameter of the stator core 111. It is divided into miniaturized, standard, enhanced heat dissipation, high-load and long-life types (including self-lubricating coating) according to the application scenario, further improving the operating stability and life of the motor under different working conditions.

[0116] Furthermore, if Figure 2a and Figure 2b As shown, the brushless motor further includes a bracket 101, a circuit board 102 and lead wires 103:

[0117] The bracket 101 is installed in conjunction with the base 113 to assist in fixing the base and the surrounding structure, thereby enhancing the overall assembly stability of the motor;

[0118] The circuit board 102 is mounted on the base 113 and forms a fixed installation space with the bracket 101, receives the magnetic pole detection signal and outputs a PWM waveform to the winding;

[0119] The lead wire 103 has one end connected to the circuit board 102 and the other end led out from the preset notch of the base 113 for connecting to the external circuit, transmitting the motor control signal and the power supply current, ensuring the wiring is regular and avoiding interference of rotating parts.

[0120] Examples 1 to 5 are internal rotor solutions. Through specific combinations of the above parameters, each solution is adapted to scenarios such as the ultra-compact integrated area in the center of the eVTOL fuselage, the embedded layout on the leading edge of the wing, the main lift area for high-altitude cruise, the auxiliary lift area for heavy-load takeoff and landing, and the long-endurance transoceanic cruise area, forming an internal rotor power solution for brushless motors covering all flight phases.

[0121] Example 1

[0122] This embodiment is an inner-rotor brushless motor adapted to the ultra-compact integrated area in the center of the eVTOL fuselage (such as the stacking of multiple brushless motors in a ducted fan).

[0123] Rotor module: The magnet thickness is 0.4mm, the circumferential width is 1.8mm, and the crankshaft size is 2.5×8mm; the bearings use miniaturized ceramic ball bearings, which are suitable for ultra-compact layout.

[0124] Stator module: The stator core is made of laminated 0.3mm silicon steel sheets with a 0.05mm thick resin coating on the surface; the winding is wound with 7 strands of 0.1mm diameter copper wire with 25 turns; the base is made of carbon fiber composite material to achieve extreme lightweight.

[0125] The brushless motor of Example 1 is extremely small and can be flexibly stacked in a ducted fan. When the rotors of multiple brushless motors work together, they can not only adapt to the limited space of the duct, but also ensure uninterrupted duct power through redundant design (for example, when a rotor fails, the remaining rotors can fill in the gap and output).

[0126] In this embodiment, the power requirements of ultra-small spaces are met through compact design and lightweight materials.

[0127] Example 2

[0128] This embodiment is an inner-rotor brushless motor adapted to multiple brushless motors embedded in the leading edge of an eVTOL wing (hidden layout to reduce wind resistance).

[0129] Rotor module: The magnet thickness is 0.5mm, the circumferential width is 2mm, and the crankshaft size is 3.0×10mm; the bearings use standard ceramic ball bearings to balance performance and cost.

[0130] Stator module: The stator core is constructed from laminated 0.35mm thick silicon steel sheets with a 0.06mm thick resin coating. The windings are wound with 30 turns of 8-strand 0.12mm diameter copper wire. The frame is constructed from 7075 aluminum alloy, achieving conventional lightweight design. 7075 aluminum alloy is a commonly used 7-series aluminum alloy and complies with the GB / T3880.2-2012 standard.

[0131] The brushless motor of Example 2 can be embedded in the leading edge of the wing to form a hidden layout, reducing flight wind resistance; multiple brushless motors work together to fill the space at the leading edge of the wing. In the event of a failure, the rotors of adjacent brushless motors can immediately fill in the position and output, ensuring lift stability.

[0132] This embodiment achieves a balance between performance and cost by optimizing bearing performance and base material.

[0133] Example 3

[0134] This embodiment is an inner rotor brushless motor adapted to the main lift zone (continuous medium power output, temperature control required) of the eVTOL high-altitude cruise phase:

[0135] Rotor module: The magnet thickness is 0.6mm, the circumferential width is 2.2mm, and the crankshaft size is 3.5×12mm; the bearings use enhanced heat dissipation ceramic ball bearings to improve stability in high temperature environments, and the outer diameter matches the inner diameter of the stator core.

[0136] Stator module: The stator core is made of laminated 0.35mm silicon steel sheets, with a 0.07mm thick resin coating (including heat dissipation microchannels) on the surface; the winding is wound with 9 strands of 0.15mm diameter copper wire, with 35 turns; the base is made of aluminum-based composite material to enhance heat dissipation performance.

[0137] The brushless motor of Example 3 shares the heat load through the rotors of multiple brushless motors. The heat dissipation microchannels of the stator coating and the aluminum-based composite material base form an efficient heat dissipation system, which can ensure stable motor power output in high-altitude and low-pressure environments.

[0138] This embodiment specifically solves the temperature control problem of high-altitude cruising through the design of the heat dissipation structure.

[0139] Example 4

[0140] This embodiment is an inner rotor brushless motor adapted to the auxiliary lift zone (short-term high load, such as a full passenger and luggage) during the heavy-load takeoff and landing phase of eVTOL:

[0141] Rotor module: The magnet thickness is 0.7mm, the circumferential width is 2.4mm, and the crankshaft size is 4.0×14mm; the bearings use high-load ceramic ball bearings to withstand short-term high torque.

[0142] Stator module: The stator core is made of laminated 0.4mm silicon steel sheets, with a 0.08mm thick resin coating on the surface (thickened to resist deformation); the winding is wound with 10 strands of 0.2mm diameter copper wire, with 40 turns; the machine base is made of high-strength forged aluminum alloy.

[0143] The brushless motor of Example 4 outputs high torque through the short-term coordinated output of the rotors of multiple brushless motors. The thick silicon steel sheets and high-strength machine base can resist deformation caused by heavy loads, ensuring power reliability during heavy-load take-off and landing.

[0144] This embodiment meets the parameter design requirements for high-load scenarios by enhancing structural strength and load capacity.

[0145] Example 5

[0146] This embodiment is an inner rotor brushless motor adapted for the eVTOL transoceanic long-duration cruising zone (continuous low load, requiring reduced energy consumption):

[0147] Rotor module: The magnet thickness is 0.8mm, the circumferential width is 2.6mm, and the crankshaft size is 4.5×16mm; the bearings use long-life ceramic ball bearings (with self-lubricating coating) to reduce friction energy consumption.

[0148] Stator module: The stator core is made of laminated 0.4mm silicon steel sheets, with a 0.09mm thick resin coating on the surface (wear-resistant reinforcement); the winding is wound with 11 strands of 0.25mm diameter copper wire, with 45 turns; the machine base is made of magnesium alloy, which combines lightweight and medium strength.

[0149] The brushless motor of Example 5 achieves the goal of low energy consumption and extends the battery life by using the low-load coordinated operation of the rotors of multiple brushless motors, the self-lubricating bearings to reduce friction loss, and the magnesium alloy base to reduce the weight of the system.

[0150] This embodiment optimizes the endurance performance in long-flight scenarios through low-energy consumption design.

[0151] First, combine Figures 5a to 6b The outer rotor scheme of the brushless motor used in eVTOL is described in detail.

[0152] Figure 5a 、 Figure 5b and Figure 5c The front view, left view and top view of a brushless motor for eVTOL according to another embodiment of the present invention are disclosed respectively. Figures 5a to 5c As shown, the present invention proposes a brushless motor for eVTOL, comprising at least:

[0153] The rotor module can be selectively arranged outside the stator module;

[0154] The stator module is provided corresponding to the rotor module, and includes a stator core 211, a winding 212, and a base (not shown in the figure). The stator core 211 is wound with the winding 212, and the base is used to fix the stator core 211;

[0155] The magnetic pole detection device 230 is disposed on a side of the winding 212 and is used to output a voltage according to the alternating magnetic flux of the winding 212 .

[0156] The outer rotor solution of the brushless motor for eVTOL is designed with precise optimization of the parameters of the rotor module and stator module, focusing on adapting eVTOL to flight phases requiring high torque output and high stability (such as vertical take-off and landing, emergency avoidance, and heavy-load take-off and landing in plateaus). Through the coordinated design of structural layout and performance parameters, it meets core requirements such as instantaneous high torque, anti-deformation, and adaptability to extreme environments.

[0157] Figure 6a The following discloses an exploded isometric view of a brushless motor for eVTOL according to another embodiment of the present invention. Figure 6b An axonometric diagram of a brushless motor for eVTOL according to another embodiment of the present invention is disclosed. Figures 6a to 6b As shown, the stator module 210 includes:

[0158] The stator core 211 is made of laminated silicon steel sheets, which reduces energy waste through low hysteresis loss characteristics and provides a stable electromagnetic foundation for high torque output;

[0159] The winding 212 is wound with multiple strands of fine copper wire to improve current carrying capacity and heat dissipation efficiency, ensuring stability during high power output;

[0160] The motor base serves as both a structural support and a heat dissipation carrier. Its material selection and structural design directly affect the motor's strength and environmental adaptability.

[0161] In this embodiment, the stator core uses laminated silicon steel sheets with a thickness of 0.3-0.45 mm and a 0.05-0.1 mm resin coating. The thickness of the silicon steel sheets is differentiated according to the torque level. Thinner silicon steel sheets are used in low-torque scenarios to reduce iron loss, while thicker silicon steel sheets are used in high-torque scenarios to enhance structural stability. The resin coating not only serves as insulation but also optimizes performance according to scenario requirements. For example, an ultra-thin coating reduces thermal resistance, while a thick coating improves high-temperature and deformation resistance.

[0162] The number of windings 212 is 6, and each winding 212 is wound with 8-11 strands of copper wire, the diameter of the copper wire is 0.12-0.25mm, and the number of turns is 28-40: the current carrying capacity is improved by increasing the number of strands and wire diameter to match the large current input required for high torque; the optimized design of the number of turns balances the electromagnetic induction intensity and the winding resistance, controlling energy consumption while ensuring torque output.

[0163] The base is made of aluminum alloy-graphene composite, titanium alloy-aluminum alloy composite, carbon fiber-titanium alloy composite or high-temperature alloy material:

[0164] The aluminum alloy-graphene composite material enhances heat dissipation performance and adapts to the continuous heat dissipation needs of conventional cruising; the titanium alloy-aluminum alloy composite material combines high strength and lightweight to resist torsional deformation during the vertical take-off phase; the carbon fiber-titanium alloy composite material has extreme strength to cope with short-term high loads during emergency avoidance; the high-temperature alloy material can withstand the extremely high temperature loads during heavy-load takeoff and landing on the plateau, ensuring the structural stability of the motor in extreme environments.

[0165] like Figures 6a to 6b As shown, the rotor module 220 includes:

[0166] The rotor core 222, composed of permanent magnets and iron, is located outside the stator module 210 and is driven by the external magnetic field. The outer rotor layout can increase the rotation radius and improve the torque output capacity.

[0167] The crankshaft 221 is fixedly connected to the rotor core 222 and acts as a rotating shaft to transmit power. Its size is designed to match the torque requirements.

[0168] The bearing 223 is disposed between the circuit board 202 and the crankshaft 221 and is used to stably support the rotating components, reduce friction loss and ensure rotation accuracy.

[0169] In this embodiment, the magnet thickness of the rotor core 222 is 0.7-1.3 mm, and the circumferential width is 2.2-3.1 mm. Through the gradient amplification design of the magnet size, a stronger magnetic field foundation is provided for high torque output. The increase in magnet thickness can increase the magnetic flux density, and the expansion of the circumferential width can enhance the range of the magnetic field, thereby meeting the torque requirements in different scenarios.

[0170] In this embodiment, the crankshaft has a diameter of 3.5-5.0 mm and a length of 11-17 mm.

[0171] Furthermore, if Figures 6a to 6b As shown, the brushless motor further includes a circuit board 202 and a connector 203:

[0172] The circuit board 202 is mounted on the bearing 223 and forms a rigid connection with the stator module, receives the magnetic pole detection signal and outputs a PWM waveform to the winding;

[0173] The connector 203 is mounted on the circuit board 202 and is used to connect the circuit board 202 with an external circuit.

[0174] Examples 6 to 9 are external rotor solutions. Through targeted combinations of the above parameters, each solution is adapted to scenarios such as the conventional lift area at the end of the eVTOL wing, the high torque area in the vertical take-off conversion phase, the emergency avoidance maneuvering area, and heavy-load take-off and landing at plateau airports, forming an external rotor power solution covering all scenarios with high torque requirements.

[0175] Example 6

[0176] This embodiment is an outer rotor brushless motor adapted to the conventional lift region (multi-rotor layout outer rotor, conventional cruise) of the eVTOL wing end.

[0177] Rotor module: The magnet thickness is 0.7mm, the circumferential width is 2.2mm, and the crankshaft size is 3.5×11mm; the bearing uses a low-friction magnetic levitation bearing, which is suitable for medium torque output.

[0178] Stator module: The stator core is made of laminated 0.3mm silicon steel sheets and has a 0.05mm thick resin coating on the surface (the ultra-thin coating reduces thermal resistance). The winding is wound with 8 strands of 0.12mm diameter copper wire, with 28 turns. The base is made of aluminum alloy-graphene composite material to enhance heat dissipation.

[0179] The brushless motor of Example 6 outputs medium torque through the coordinated output of the rotors of multiple brushless motors, the low-friction magnetic bearing reduces cruise energy consumption, and the aluminum alloy-graphene composite base ensures heat dissipation efficiency during continuous flight, making it suitable for conventional cruise scenarios.

[0180] In this embodiment, the magnet parameters, stator structure, etc. meet the low-friction design requirements, thereby optimizing cruising energy consumption.

[0181] Example 7

[0182] This embodiment is an outer rotor brushless motor adapted to the high torque zone of the eVTOL vertical transition phase (transition from vertical to horizontal thrust, instantaneous high torque).

[0183] Rotor module: The magnet thickness is 0.9mm, the circumferential width is 2.5mm, and the crankshaft size is 4.0×13mm; the bearing uses a medium-friction magnetic levitation bearing (enhanced torque) to improve instantaneous output capacity.

[0184] Stator module: The stator core is made of laminated 0.35mm silicon steel sheets and has a 0.07mm thick resin coating on the surface (balancing thermal resistance and strength). The winding is wound with 9 strands of 0.18mm diameter copper wire, with 32 turns. The base is made of a titanium alloy-aluminum alloy composite material, which combines high strength and lightweight.

[0185] The brushless motor of Example 7 generates a large torque through the instantaneous coordinated burst of high torque by the rotors of multiple brushless motors, and the composite machine base resists torsional deformation, thereby ensuring the posture stability during the vertical transition stage and avoiding posture loss of control due to power fluctuations.

[0186] This embodiment meets the design requirements for high-torque scenarios by enhancing torque output and structural strength.

[0187] Example 8

[0188] This embodiment is an outer rotor brushless motor adapted for the eVTOL emergency avoidance maneuvering area (such as avoiding obstacles, which requires instantaneous ultra-large pulling force).

[0189] Rotor module: The magnet thickness is 1.1mm, the circumferential width is 2.8mm, and the crankshaft size is 4.5×15mm; the bearing uses a high-friction magnetic levitation bearing (limit torque) to adapt to instantaneous ultra-large loads.

[0190] Stator module: The stator core is made of laminated 0.4mm silicon steel sheets and has a 0.09mm thick resin coating on the surface (the thick coating is resistant to high temperatures). The winding is wound with 10 strands of 0.22mm diameter copper wire, with 36 turns. The base is made of a carbon fiber-titanium alloy composite material for extreme strength.

[0191] The brushless motor of Example 8 outputs the ultimate torque through the coordinated output of multiple brushless motors. The thick resin coating and strong base can withstand short-term high temperatures and high loads, ensuring power redundancy during emergency avoidance and improving the safety factor.

[0192] This embodiment achieves power reliability in emergency scenarios through extreme parameter design.

[0193] Example 9

[0194] This embodiment is an outer rotor brushless motor adapted to heavy-load takeoff and landing of eVTOL at plateau airports (where the air is thin and requires ultra-large blade thrust).

[0195] Rotor module: The magnet thickness is 1.3mm, the circumferential width is 3.1mm, and the crankshaft size is 5.0×17mm; the bearing uses a special-standard magnetic levitation bearing to meet the installation requirements of oversized blades.

[0196] Stator module: The stator core is made of laminated 0.45mm silicon steel sheets, with a 0.1mm thick resin coating on the surface (the extra-thick coating ensures insulation); the winding is wound with 11 strands of 0.25mm diameter copper wire, with 40 turns; the machine base is made of high-temperature alloy to withstand extremely high temperature loads.

[0197] The brushless motor of Example 9 adapts the extra-large blades through a large-size rotor. The rotors of multiple brushless motors work together to compensate for the power attenuation caused by the thin air in the plateau. The high-temperature alloy base resists the high heat conducted by the hub, ensuring the power output for heavy-load takeoff and landing.

[0198] This embodiment meets the parameter adaptation requirements for extreme scenarios through large-size design and high-temperature resistant materials.

[0199] Based on the above-mentioned inner rotor or outer rotor brushless motor, a power control system suitable for all eVTOL scenarios can be built.

[0200] The first power control system based on a brushless motor proposed by the present invention includes:

[0201] Such as the brushless motors used for eVTOL mentioned above;

[0202] Airframe circuits, including the airframe controller, are used to manage the entire aircraft's operating status (such as flight attitude, load, environmental parameters, etc.);

[0203] a motor circuit, connected to the body circuit, comprising a motor controller and a three-phase drive circuit;

[0204] The motor controller is used to convert the flight instructions output by the fuselage controller into motor control signals (such as speed and torque target values);

[0205] The three-phase drive circuit is connected to the U / V / W phases of the brushless motor, converts the control signal into a drive current, and realizes the operation control of the motor.

[0206] The second power control system based on a brushless motor proposed by the present invention includes:

[0207] Such as the brushless motors used for eVTOL mentioned above;

[0208] Body circuit, including body controller and motor controller:

[0209] The fuselage controller is used to manage the operating status of the entire aircraft (such as flight attitude, load, environmental parameters, etc.), and the motor controller is used to convert the flight instructions output by the fuselage controller into motor control signals (such as speed and torque target values);

[0210] a motor circuit connected to the body circuit and comprising a three-phase drive circuit;

[0211] The three-phase drive circuit is connected to the U / V / W phases of the brushless motor, converts the control signal into a drive current, and realizes the operation control of the motor.

[0212] The core difference between these two powertrain systems lies in the integration location of the motor controllers. The former places the motor controllers independently within the motor circuits, making it suitable for scenarios where space constraints are critical for fuselage circuitry. The latter integrates the motor controllers within the fuselage circuits, enabling centralized processing to improve the coordinated response speed of multiple motors and making it more suitable for eVTOL flight scenarios requiring high-frequency dynamic adjustments (such as vertical takeoff and landing transitions and emergency avoidance). Both layouts maintain system flexibility, allowing for the selection of an appropriate solution based on the eVTOL aircraft design.

[0213] Furthermore, there are multiple brushless motors in the above-mentioned power control system, including a combination of inner rotor and outer rotor brushless motors, which are dispersed in different positions of the fuselage (such as inside the duct, leading edge of the wing, wing end, etc.) according to the flight scenario requirements of the eVTOL (such as duct space, wing structure, lift distribution).

[0214] Multiple brushless motors can work in close coordination through motor controllers:

[0215] The motor controller dynamically matches the brushless motor output combination of inner / outer rotor motors based on the power requirements of different eVTOL flight scenarios (such as energy consumption optimization for low-load cruising, torque output for heavy-load takeoff and landing, and power compensation at high altitudes);

[0216] Furthermore, the motor controller also includes a continuously variable speed control module, which adopts a multi-motor cooperative control algorithm to achieve smooth speed control of the motor.

[0217] The multi-motor coordinated control algorithm is a complex control logic that integrates scene perception, dynamic allocation, and real-time adjustment. The core achieves precise control through the collaboration of hardware and software, including but not limited to the following steps:

[0218] Real-time collection of each motor's output torque, temperature, and current feedback (via winding current sensors and magnetic flux signals from magnetic pole detection devices) is used to distribute the load ratio of each motor according to preset weights based on the total power requirements of the eVTOL's current flight phase (such as vertical takeoff and landing, cruise, and heavy load).

[0219] When a motor fails (such as abnormal current or sudden speed drop), fault diagnosis is performed and the replacement mechanism is immediately triggered;

[0220] Based on the fuselage attitude sensor and environmental parameters (altitude, wind speed), the output combination of the inner / outer rotor motor is dynamically adjusted.

[0221] Continuously variable speed is achieved through the motor controller's continuously variable speed control module and hardware features:

[0222] The hardware relies on the low resistance characteristics of the multi-strand fine copper wire winding to reduce regulation losses. The magnetic pole detection device samples the changes in the winding magnetic flux at a high frequency (for example, 1kHz) to provide accurate feedback for speed regulation.

[0223] The software control uses a PID closed-loop regulation algorithm to convert the target speed into a continuous PWM signal.

[0224] Multi-motor synchronization uses a time synchronization protocol (such as the CAN bus) to ensure that the phase difference of each motor's PWM signal is less than a specified threshold (such as 1ms), avoiding vibration of the fuselage caused by speed differences.

[0225] The above-mentioned continuously variable speed control module and its multi-motor coordinated control algorithm, combined with the hardware characteristics of the inner / outer rotor motors, not only ensure the continuity of single-machine speed regulation, but also achieve the accuracy of multi-motor coordination.

[0226] For example, the continuously variable speed control module and multi-motor collaborative control algorithm enable smooth speed regulation and intelligent load distribution (such as the multi-motor thermal load sharing in Example 3 and the coordinated instantaneous torque burst in Example 7). If a single motor fails, the system can quickly dispatch the remaining motors to fill the gap, ensuring power redundancy and safety.

[0227] Integrating the power control system into the eVTOL fuselage can enable corresponding brushless motor solutions for different flight scenarios such as duct stacking, wing embedding, high-altitude cruising, and emergency avoidance. Through the coordinated control of multiple brushless motors, the stability, safety redundancy, and energy efficiency performance of the eVTOL power output can be comprehensively improved.

[0228] Based on the above power control system and brushless motor, the present invention also proposes an eVTOL.

[0229] Figure 7a and Figure 7b The isometric view and top view of the eVTOL structure according to an embodiment of the present invention are respectively disclosed. Figure 7a and Figure 7b As shown, the eVTOL proposed by the present invention includes at least a fuselage 31, blades 32, and a power control system 33 based on a brushless motor as described above:

[0230] The power control system 33 controls the brushless motor to provide flight power for the eVTOL.

[0231] More specifically, the fuselage 31 is the entire aircraft carrying structure, integrating an onboard power supply module, attitude sensor, and avionics system, and providing energy and environmental perception data for the power control system 33;

[0232] The blades 32 are in driving connection with the rotor module of the brushless motor, and are driven by the motor to generate lift or thrust. The size and number of the blades 32 are matched to the type of brushless motor (inner rotor / outer rotor) (e.g., an inner rotor motor is suitable for small ducted blades, and an outer rotor motor is suitable for large diameter cruise blades);

[0233] The power control system 33 serves as the core power center, and the multiple brushless motors it contains are distributed at key positions of the fuselage according to a scenario-based layout: for example, an inner rotor brushless motor is arranged in the central duct area of ​​the fuselage (as in Example 1), an inner rotor brushless motor is embedded in the leading edge of the wing (as in Example 2), and an outer rotor brushless motor is suspended at the end of the wing (as in Example 6).

[0234] During the specific flight process, the power control system 33 dynamically dispatches each brushless motor according to the avionics instructions of the fuselage 31:

[0235] During the vertical takeoff and landing phase, the ducted inner rotor motor and the wing leading edge inner rotor motor work together to output a large torque to drive the blades 32 to generate vertical lift;

[0236] During the horizontal cruise phase, the outer rotor motor at the wing end is the main output, and the inner rotor motor assists in adjusting the attitude, achieving low-energy flight through stepless speed control;

[0237] In case of emergency avoidance, the outer rotor motor (such as Example 8) instantly bursts out the limit torque, and cooperates with the inner rotor motor's compensation output to ensure that the fuselage 31 quickly adjusts its posture to avoid obstacles.

[0238] The eVTOL proposed in this invention, through multi-motor collaboration and scenario-based layout, can operate flexibly in complex environments such as densely populated urban areas, high-altitude areas, and remote sites, taking into account the advantages of low noise and zero emissions. At the same time, it solves the problems of insufficient power adaptability and low safety redundancy of traditional eVTOLs, and provides a reliable vehicle for scenarios such as urban air traffic and emergency rescue.

[0239] The brushless motor, power control system, and eVTOL proposed in the present invention have the following beneficial effects:

[0240] 1) Through the modular layout of inner / outer rotors and scenario-based parameter customization, combined with a diverse base material, anti-deformation structure, and strong heat dissipation design, this solves the problem of a single-specification motor's insufficient ability to adapt to all eVTOL flight scenarios, ensuring stable operation and long life in complex operating conditions.

[0241] 2) Relying on a multi-motor coordinated control algorithm, the system achieves dynamic output combinations of inner and outer rotor motors, precisely matching power requirements at different flight stages. This improves safety redundancy while optimizing energy efficiency and fully unleashing hardware performance.

[0242] 3) By integrating brushless motors and power control systems, the system solves the problems of poor power adaptability, low safety redundancy, and difficulty in balancing endurance and load in traditional eVTOLs. It can cover all scenarios such as flight in densely populated urban areas, high-altitude cruising, emergency avoidance, heavy-load takeoff and landing, and has high safety, high energy efficiency and strong environmental adaptability.

[0243] As used in this application and the claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not intended to refer to the singular but may include the plural. Generally speaking, the terms "comprises" and "include" only indicate the inclusion of the steps and elements specifically identified, and these steps and elements do not constitute an exclusive list. A method or apparatus may also include other steps or elements.

[0244] Those skilled in the art will further appreciate that the various illustrative logic blocks, modules, circuits, and algorithmic steps described in conjunction with the embodiments disclosed herein can be implemented as electronic hardware, computer software, or a combination of the two. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps are generally described above in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the specific application and the design constraints imposed on the overall system. A skilled person may implement the described functionality in different ways for each specific application, but such implementation decisions should not be interpreted as resulting in a departure from the scope of the present invention.

[0245] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "clockwise", "counterclockwise" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0246] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more, unless otherwise explicitly specified.

[0247] In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediary; or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0248] The above embodiments are provided to persons familiar with the art for implementing or using the present invention. Personnel familiar with the art may make various modifications or changes to the above embodiments without departing from the inventive concept of the present invention. Therefore, the scope of protection of the present invention is not limited to the above embodiments, but should be the maximum scope of the innovative features mentioned in the claims.

Claims

1. A brushless motor for eVTOL, characterized in that: At least: The rotor module can be selectively arranged inside or outside the stator module to adapt to the differentiated motor parameter requirements of different eVTOL flight scenarios; The stator module is arranged corresponding to the rotor module and includes at least a stator core, windings, and a base. The stator core is wound with windings, and the base is used to fix the stator core and adapt to the structural and heat dissipation requirements of different eVTOL flight scenarios; A magnetic pole detection device is arranged on the side of the winding and is used to output a magnetic pole detection signal according to the alternating magnetic flux of the winding, so as to realize the detection and control of the running state of the motor; The circuit board is fixed to the non-rotating end of the machine base, receives the magnetic pole detection signal and outputs PWM waveforms to the U / V / W phase windings.

2. The brushless motor for eVTOL according to claim 1, characterized in that: The rotor module is located inside the stator module and includes: The rotor core, composed of permanent magnets and iron, is located inside the stator module and is driven by the internal magnetic field. The crankshaft is integrated with the permanent magnet and serves as the rotating axis; The bearing is mounted on the crankshaft and is used to fix the crankshaft; The stator module comprises: The stator core is made of laminated silicon steel sheets; The winding is made of multiple strands of fine copper wire; The base serves as structural support and heat dissipation carrier.

3. The brushless motor for eVTOL according to claim 2, characterized in that: The magnet thickness of the rotor core is 0.4-0.8 mm and the circumferential width is 1.8-2.6 mm; The crankshaft has a diameter of 2.5-4.5 mm and a length of 8-16 mm.

4. The brushless motor for eVTOL according to claim 2, characterized in that: The thickness of the laminated silicon steel sheets of the stator core is 0.3-0.4 mm, with a 0.05-0.09 mm resin coating; The winding is made of 7-11 strands of copper wire, the diameter of the copper wire is 0.1-0.25 mm, and the number of turns is 25-45.

5. The brushless motor for eVTOL according to claim 2, characterized in that: The machine base is made of carbon fiber composite, aluminum alloy, aluminum-based composite material, forged aluminum alloy or magnesium alloy.

6. The brushless motor for eVTOL according to claim 2, characterized in that: The bearing is a ceramic ball bearing, and the inner diameter thereof is adapted to the crankshaft.

7. The brushless motor for eVTOL according to claim 1, characterized in that: The rotor module is located outside the stator module and includes: The rotor core is composed of permanent magnets and iron, and is driven by the external magnetic field to achieve rotation; The crankshaft is fixedly connected to the rotor core and is the rotating axis; A bearing is provided between the circuit board and the crankshaft to support rotation; The stator module comprises: The stator core is made of laminated silicon steel sheets; The winding is made of multiple strands of fine copper wire; The base serves as structural support and heat dissipation carrier.

8. The brushless motor for eVTOL according to claim 7, characterized in that: The magnet thickness of the rotor core is 0.7-1.3 mm and the circumferential width is 2.2-3.1 mm; The crankshaft has a diameter of 3.5-5.0 mm and a length of 11-17 mm.

9. The brushless motor for eVTOL according to claim 7, characterized in that: The stator core uses laminated silicon steel sheets with a thickness of 0.3-0.45 mm and a 0.05-0.1 mm resin coating; The winding is made of 8-11 strands of copper wire, the diameter of the copper wire is 0.12-0.25 mm, and the number of turns is 28-40.

10. The brushless motor for eVTOL according to claim 7, characterized in that: The machine base is made of aluminum alloy-graphene composite, titanium alloy-aluminum alloy composite, carbon fiber-titanium alloy composite or high-temperature alloy material.

11. The brushless motor for eVTOL according to claim 7, characterized in that: The bearing is a magnetic bearing.

12. A power control system based on a brushless motor, characterized in that: include: The brushless motor for eVTOL according to any one of claims 1 to 11; The fuselage circuit, including the fuselage controller, is used to manage the operating status of the entire machine; a motor circuit, connected to the body circuit, comprising a motor controller and a three-phase drive circuit; The motor controller is used to convert the instructions of the fuselage controller into motor control signals; The three-phase drive circuit is connected to the U / V / W phases of the brushless motor.

13. A power control system based on a brushless motor, characterized in that: include: The brushless motor for eVTOL according to any one of claims 1 to 11; Body circuit, including body controller and motor controller: The body controller is used to manage the operation status of the entire machine, and the motor controller is used to convert the instructions of the body controller into motor control signals; a motor circuit connected to the body circuit and comprising a three-phase drive circuit; The three-phase drive circuit is connected to the U / V / W phases of the brushless motor.

14. The power control system based on a brushless motor according to claim 12 or 13, characterized in that: There are multiple brushless motors, and the multiple brushless motors are distributed at different positions of the fuselage according to the flight scenario requirements of the eVTOL.

15. The power control system based on a brushless motor according to claim 14, characterized in that: The plurality of brushless motors are coordinated to work through a motor controller; The motor controller dynamically matches the output combination of multiple brushless motors according to the power requirements of different eVTOL flight scenarios.

16. The power control system based on a brushless motor according to claim 15, characterized in that: The motor controller also includes a continuously variable speed control module, which uses a multi-motor cooperative control algorithm to achieve smooth speed control of the motor.

17. An eVTOL, characterized in that: At least comprising a fuselage, blades, and a power control system based on a brushless motor as claimed in any one of claims 12 to 16: The power control system controls the brushless motor to provide flight power for the eVTOL.

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