Electric engine, electric propulsion device and aircraft

Abstract

The utility model provides an electric engine, an electric propulsion device and an aircraft, and relates to the technical field of aircrafts. The electric engine comprises a motor controller and a power motor, the motor controller is used for controlling the power motor, the motor controller is further used for controlling a heat dissipation motor and / or a variable pitch motor, and the motor controller is of a dual-redundancy design. Control of the power motor, the heat dissipation motor and / or the variable-pitch motor is integrated, the power motor, the heat dissipation motor and / or the variable-pitch motor are controlled through the motor controller, the complexity of cable connection is reduced, the size and weight of the electric engine are reduced, miniaturization and light weight are achieved, and therefore energy consumption is reduced, and efficient flight is achieved. The motor controllers are of a dual-redundancy design, when one motor controller breaks down, the other motor controller continues to work, the effects of high-efficiency control and high redundancy are achieved, then the reliability and safety of the electric engine are improved, and safe and stable operation of the aircraft is guaranteed.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft, in particular to an electric engine, an electric propulsion device and an aircraft. BACKGROUND

[0002] In the field of aircraft, especially in aircraft such as electric vertical take-off and landing (eVTOL) aircraft, the design and assembly of electric engines are limited by volume, weight and safety, and are designed and assembled in a way that reduces volume and / or weight while improving safety, to achieve safe and efficient flight. SUMMARY

[0003] The present application provides an electric engine, an electric propulsion device and an aircraft, to realize a small, light and safe electric engine.

[0004] In a first aspect, the present application provides an electric engine, comprising: a motor controller and a power motor, the motor controller being configured to control the power motor, the motor controller being further configured to control a variable pitch motor and / or a cooling motor, and the motor controller being designed with dual redundancy.

[0005] In a possible implementation, the power motor, the variable pitch motor and the cooling motor are designed with dual stator winding.

[0006] In a possible implementation, the heat generating components in the motor controller are cooled by a cooling plate.

[0007] In a possible implementation, the heat generating components include power devices of the motor controller.

[0008] In a possible implementation, the heat generating components in the motor controller are integrated with the cooling plate, or the heat generating components in the motor controller are arranged in contact with the cooling plate.

[0009] In a possible implementation, the motor controller includes driving boards and power devices corresponding to the controlled motors, respectively.

[0010] In a possible implementation, the cooling motor includes a circulating pump motor, the circulating pump motor being configured to provide power to a circulating pump, or the circulating pump motor being configured to provide power to the circulating pump and a fan, respectively; or the cooling motor includes a circulating pump motor and a fan motor.

[0011] In a possible implementation, the circulating pump motor is arranged adjacent to the heat sink.

[0012] In a possible implementation, if the cooling motor includes a circulating pump motor and a fan motor, the circulating pump motor and the fan motor are arranged on the same side or different sides of the heat sink, respectively.

[0013] In a possible implementation, if the heat dissipation motor comprises a circulating pump motor and a fan motor, the circulating pump motor and the fan motor are controlled by the motor controller respectively.

[0014] In a possible implementation, the motor controller, the circulating pump motor, the heat sink and the fan motor are coaxially arranged in sequence along the rotation axis direction of the power motor.

[0015] In a possible implementation, adjacent parts of the power motor, the motor controller, the circulating pump motor, the fan motor and the heat sink coaxially arranged are connected as a whole by a structural member.

[0016] In a possible implementation, the electric motor interacts with a flight control system, and the flight control system is used to control the electric motor.

[0017] In a possible implementation, the electric motor interacts with a flight control system, and the flight control system is used to control the electric motor.

[0018] In a possible implementation, the variable pitch mechanism adopts a worm and gear structure, or a planetary gear structure, or a screw rod structure.

[0019] In a possible implementation, the variable pitch propeller further comprises a guide fan assembled to the hub.

[0020] In a possible implementation, the electric motor interacts with a flight control system, and the flight control system is used to control the electric motor.

[0021] In a possible implementation, the aircraft further comprises a tilting motor for controlling the tilting mechanism.

[0022] The electric motor, the electric propulsion device and the aircraft provided by the application comprise: a motor controller and a power motor, the motor controller is used for controlling the power motor, the motor controller is also used for controlling a cooling motor and / or a variable pitch motor, and the motor controller is designed in a dual-redundancy mode. By integrating the control of the power motor, the cooling motor and / or the variable pitch motor by the motor controller, the complexity of cable connection is reduced, the size and weight of the electric motor are reduced, the electric motor is miniaturized and lightened, the energy consumption is reduced, the cruising range of the aircraft is improved, and efficient flight is realized. The motor controller is designed in a dual-redundancy mode, when one motor controller fails, the other motor controller continues to work, the effects of efficient control and high redundancy are realized, and the reliability and safety of the electric motor are improved, thereby ensuring the safe and stable operation of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0023] The drawings incorporated into the specification and constituting a part of the specification show embodiments consistent with the application and, together with the specification, serve to explain the principles of the application.

[0024] Figure 1 Structure diagram of the electric motor provided for the exemplary embodiments of the application Figure 1 ;

[0025] Figure 2 Structure diagram of the motor controller provided for the exemplary embodiments of the application

[0026] Figure 3 Structure diagram of the electric motor provided for the exemplary embodiments of the application Figure 2 ;

[0027] Figure 4 Cross-sectional layout diagram of the electric motor provided for the exemplary embodiments of the application

[0028] Figure 5 Structure diagram of the electric propulsion device provided for the exemplary embodiments of the application

[0029] REFERENCE NUMERALS:

[0030] 10: electric motor; 11: motor controller; 12: power motor; 13: cooling motor; 14: variable pitch motor; 43: circulating pump motor; 44: radiator; 45: fan motor; 46: rotor shell;

[0031] 211: first bus capacitor; 212: second bus capacitor; 221: first cooling plate; 222: second cooling plate; 231: first inverter module; 232: second inverter module; 241: first motor drive board; 242: second motor drive board; 251: first main control board; 252: second main control board;

[0032] 50: electric propulsion device; 51: variable pitch propeller; 53: fairing; 54: pitch mechanism; 55: propeller; 56: hub.

[0033] The specific embodiments of the present application have been shown through the above-described drawings, and will be described in more detail hereinafter. The drawings and the written description are not intended to restrict the scope of the present application by any means, but to illustrate the concept of the present application to those skilled in the art by referring to specific embodiments. DETAILED DESCRIPTION

[0034] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0035] It should be noted that the terms "first", "second" are used only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "plurality" is at least two, for example, two, three, etc., unless otherwise explicitly specified.

[0036] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "fixing" and the like should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integrated; can be directly connected, or indirectly connected through an intermediate medium; can be the connection or interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0037] In the present application, unless otherwise explicitly specified and limited, the first feature is "on" or "under" the second feature, which can be direct contact between the first and second features, or indirect contact between the first and second features through an intermediate medium. Moreover, the first feature "above", "over" and "on" the second feature can be that the first feature is directly above or obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "under" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0038] In the above description, the description with reference to the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Also, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, the person skilled in the art can combine and combine the different embodiments or examples described in the present specification and the features of the different embodiments or examples, without contradiction.

[0039] First, the terms involved in the present application are explained:

[0040] Propeller: is to rely on the blade in the air or water (liquid) rotation, the engine or motor power into thrust (pull or lift) of the device, application range is very wide, as an important thrust (pull or lift) mechanism in the aircraft, widely used in eVTOL, helicopters, drones and other fields; In the field of ships, submarines, etc. also widely used.

[0041] Variable pitch mechanism: to improve the efficiency of the propeller, usually increase the variable pitch mechanism inside the propeller, so that the propeller changes the blade angle at different speeds and thrust (pull or lift) requirements, so that the propeller gets the best efficiency. The variable pitch mechanism of the propeller can realize the adjustment of the variable pitch of the propeller, and needs a power source to provide a variable pitch torque, and can control the variable pitch torque to realize accurate blade angle control.

[0042] Electric motor: is a system composed of electric motor, motor controller, cable and its accessories, which can convert electrical energy into mechanical energy. In actual implementation, the electric motor can also be called an electric propulsion system.

[0043] Lift / thrust assembly: composed of electric motor, propeller and its accessories.

[0044] Electric propulsion device: composed of power battery, electric motor, propeller and its accessories.

[0045] Currently, the electric motor, the variable pitch mechanism and the cooling circulation system used in the electric aviation are arranged in a distributed manner. Each type of motor is separately arranged with its corresponding motor controller. For example, a separate variable pitch motor controller controls the variable pitch motor, a separate power motor controller controls the power motor, and a separate circulation pump motor controller controls the circulation pump. Each type of motor is connected with its corresponding motor controller through a cable, and the electromagnetic interference of the connection wire harness cannot be avoided. At the same time, the complex cable connection increases the volume and weight of the electric motor. In addition, the distributed arrangement leads to a large structure of the electric motor. In addition, the motor controller corresponding to each motor is usually designed with single redundancy. When the motor controller fails, the corresponding motor cannot work normally, thereby affecting the safe flight of the aircraft.

[0046] In addition, many high-power heat generating sports devices currently, such as the drive motor of a new energy vehicle and the engine of a fuel vehicle, usually have a heat dissipation system (radiator and fan) arranged to blow the airflow generated by the fan through the radiator to carry away the heat generated by the sports device. The heat dissipation of the motor and the engine of this type of vehicle is relatively spacious in structure arrangement and has no hard quality requirements. Therefore, in order to meet the heat dissipation requirements, the size of the radiator and the size of the fan will not be excessively developed, and the front end of the radiator will not be blocked by too many obstacles. However, in order to meet the weight and arrangement space requirements, the electric vertical take-off and landing (eVTOL) aircraft usually requires the designed product to be small and precise, and to ensure the performance. Therefore, the inlet end of the radiator is blocked by the motor and the pump, which inevitably causes new problems that do not occur in other industries, such as uneven distribution of the inlet airflow, and serious heat backflow in the middle area of the radiator.

[0047] To solve the above technical problems, the application provides an electric motor scheme. The electric motor is highly integrated, the control of the power motor, the heat dissipation motor and / or the variable pitch motor is integrated into one, the motor controller is used to control the power motor, the heat dissipation motor and / or the variable pitch motor, the complexity of the cable connection is reduced, the volume and weight of the electric motor are reduced, miniaturization and light weight are realized, thereby reducing energy consumption and realizing efficient flight. The motor controller is designed with double redundancy, the reliability and safety of the electric motor are improved through the redundant design, and the safe and stable operation of the aircraft is ensured.

[0048] The technical solutions of the present application and how the technical solutions of the present application solve the above technical problems will be described in detail below with specific examples. The following specific examples can be combined with each other, and the same or similar concepts or processes can not be described again in some examples. The embodiments of the present application will be described below with reference to the drawings.

[0049] Figure 1 Structure diagram of an electric motor provided for an exemplary embodiment of the present application Figure 1 As shown in Figure 1 , the electric motor 10 provided by the exemplary embodiment of the present application includes a motor controller 11 and a power motor 12, the motor controller 11 is used to control the power motor 12, the motor controller 11 is also used to control a heat dissipation motor 13 and / or a variable pitch motor 14, and the motor controller 11 is designed with double redundancy.

[0050] Among them, the motor controller 11 integrates the control of the power motor 12, the heat dissipation motor 13 and / or the variable pitch motor 14, the motor controller 11 is connected with the power motor 12, the heat dissipation motor 13 and the variable pitch motor 14 respectively, considering the structure volume of the electric motor 10, for example, at least one of the heat dissipation motor 13 and the variable pitch motor 14 is arranged in the electric motor 10, or both the heat dissipation motor 13 and the variable pitch motor 14 are arranged outside the electric motor 10.

[0051] In an implementation manner, the motor controller 11 in the electric motor 10 is designed with double redundancy, that is, two relatively independent motor controllers are arranged in the electric motor 10, a fireproof diaphragm is arranged between the double redundancy motor controllers, or no fireproof diaphragm is arranged, the fireproof diaphragm can prevent the overheating problem from spreading between the two motor controllers, and the fireproof diaphragm can also be made of high-temperature-resistant material to reduce heat propagation; no fireproof diaphragm can simplify the system structure and reduce the overall cost of the system. It should be noted that whether to arrange the fireproof diaphragm can be selected according to actual application scenarios, system safety requirements, performance requirements and cost, and the embodiments of the present application are not limited.

[0052] The double redundancy motor controllers independently control the operation of the power motor 12, the variable pitch motor 14 and the heat dissipation motor 13. For example, the power motor 12, the heat dissipation motor 13 and the variable pitch motor 14 are all designed with double stator windings, in case of any redundancy motor controller failure (including any hardware or software failure in the motor controller), the first stator winding controlled by the failed motor controller stops working, and the corresponding second stator winding is controlled by another normal motor controller to increase the power output, compensate for the partial power loss caused by the failed motor controller, and complete the required power of the aircraft operation, the heat dissipation demand and the change of the propeller blade angle.

[0053] It can be understood that the first redundancy motor controller controls the first power motor stator winding, the first variable pitch motor stator winding and the first heat dissipation motor stator winding, and the second redundancy motor controller controls the second power motor stator winding, the second variable pitch motor stator winding and the second heat dissipation motor stator winding.

[0054] For example, the first redundancy motor controller controls the first power motor stator winding, the first variable pitch motor stator winding and the first heat dissipation motor stator winding to output a first proportion of power (for example, 50%, 40%, 60% or the like), and the second redundancy motor controller controls the second power motor stator winding, the second variable pitch motor stator winding and the second heat dissipation motor stator winding to output a second proportion of power (for example, 50%, 60%, 40% or the like). It should be noted that the sum of the first proportion and the second proportion is 100%.

[0055] In one example, if the main control board of the first redundancy motor controller fails, the first power motor stator winding, the first variable pitch motor stator winding and the first heat dissipation motor stator winding stop working, and the second redundancy motor controller controls the second power motor stator winding, the second variable pitch motor stator winding and the second heat dissipation motor stator winding to increase power output.

[0056] In another example, only the first heat dissipation motor stator winding fails, and the double stator windings of the other motors are normal, then the double stator windings of the other motors continue to work cooperatively and still normally output the agreed proportion of power, and the second redundancy motor controller controls the second heat dissipation motor stator winding to increase power output (output full proportion of power) to compensate for the partial power loss caused by the failure of the first heat dissipation motor stator winding.

[0057] It should be noted that, Figure 1 For example only, the layout of the heat dissipation motor 13 and the variable pitch motor 14 is not limited to Figure 2 As shown, the position of the heat dissipation motor 13 and the variable pitch motor 14 is not specifically limited in the embodiments of the present application.

[0058] In the embodiments of the present application, the control of the power motor, the heat dissipation motor and / or the variable pitch motor is integrated, the motor controller is used to control the power motor, the heat dissipation motor and / or the variable pitch motor, the complexity of cable connection is reduced, the size and weight of the electric motor are reduced, miniaturization and light weight are realized, thereby reducing energy consumption and realizing high efficiency flight. The control of multiple motors by the motor controller can optimize the efficiency of the electric motor system and improve the endurance of the aircraft. In addition, the motor controller is designed with double redundancy, when one motor controller fails, the other motor controller continues to work, realizing high efficiency control and high redundancy effect, thereby improving the reliability and safety of the electric motor and ensuring the safe and stable operation of the aircraft.

[0059] In some embodiments, the power motor, the pitch motor and the cooling motor are double-stator winding designs.

[0060] In the motor, the important components include a stator, which is a fixed part of the motor and is usually composed of a core and a winding. The double-stator winding can be an inner rotor or an outer rotor. For example, if the power motor is an outer rotor motor, the rotor shell is detachably connected to the propeller hub through the mounting hole on the rotor shell and the bolt, and if the power motor is an inner rotor motor, the rotor shell is detachably connected to the propeller hub through the rotating shaft.

[0061] The double-stator winding design can be regarded as having two independent stator windings inside each motor, and the two windings are stacked together to form a circumferential ring. When both stator windings are normal, the first stator winding and the second stator winding work together, and if any stator winding fails, the other normal stator winding continues to work and increases the power output to compensate for the power loss caused by the failed stator winding.

[0062] For example, the motor controller is a double-redundancy design, and the power motor, the pitch motor and the cooling motor are double-stator winding designs. For example, taking the power motor as an example, the first redundancy motor controller controls the first power motor stator winding to output power according to the corresponding proportion, and the second redundancy motor controller controls the second power motor stator winding to output power according to the corresponding proportion. In the application of the aircraft, in order to maximize the thermal balance and working efficiency of each stator winding, usually, the first power motor stator winding and the second power motor stator winding output 50% of the power respectively, that is, each stator winding is in a non-full-power running state. When any power motor stator winding fails, the other normal power motor stator winding continues to work and increases the power output to a full-power running state, compensating for the power loss caused by the failed motor stator winding, for example, to ensure the safe landing of the aircraft within a certain time.

[0063] In the embodiments of the present application, the motor adopts a double-stator winding design, which enables the double-stator windings to work together in normal operation, and the motor can still maintain safe and stable operation in the event of a stator winding failure, thereby ensuring the reliability, stability and safety of the electric motor and the safe and stable flight of the aircraft.

[0064] In some embodiments, the motor controller includes the driving board and the power device corresponding to the controlled motor.

[0065] It can be understood that if the motor controller integrates the control of the power motor, the cooling motor and / or the pitch motor, the motor controller includes the driving board and the power device corresponding to the power motor, the cooling motor and / or the pitch motor. The power device includes an inverter module.

[0066] Correspondingly, for each motor controller in the dual-redundancy motor controller, the main control board, the power motor drive board, the heat dissipation motor drive board, the variable pitch motor drive board, the power motor inverter module (power motor corresponding power device), the heat dissipation motor inverter module (heat dissipation motor corresponding power device) and the variable pitch motor inverter module (variable pitch motor corresponding power device) are included.

[0067] For example, the motor controller integrates the control of the power motor, the heat dissipation motor and the variable pitch motor. In the first redundancy motor controller, the main control board is connected with the power motor drive board, the power device driven by the power motor drive board is connected with the first power motor stator winding; the main control board is connected with the variable pitch motor drive board, the power device driven by the variable pitch motor drive board is connected with the first variable pitch motor stator winding; the main control board is connected with the heat dissipation motor drive board, the power device driven by the heat dissipation motor drive board is connected with the first heat dissipation motor stator winding. In the second redundancy motor controller, the main control board is connected with the power motor drive board, the power device driven by the power motor drive board is connected with the second power motor stator winding; the main control board is connected with the variable pitch motor drive board, the power device driven by the variable pitch motor drive board is connected with the second variable pitch motor stator winding; the main control board is connected with the heat dissipation motor drive board, the power device driven by the heat dissipation motor drive board is connected with the second heat dissipation motor stator winding.

[0068] Further, if the first redundancy motor controller fails (including any hardware or software failure of the main control board in the motor controller), the motor drive boards controlled by it all fail, causing the first power motor stator winding, the first variable pitch motor stator winding and the first heat dissipation motor stator winding to stop working, the second power motor stator winding is continued to be driven by the power motor drive board in the second redundancy motor controller to run, the second heat dissipation motor stator winding is continued to be driven by the heat dissipation motor drive board to run, the second variable pitch motor stator winding is continued to be driven by the variable pitch motor drive board to run, and the power output is increased to compensate for the partial power loss caused by the failure of the first redundancy motor controller.

[0069] If any motor drive board in the first redundancy motor controller fails (for example, the first power motor drive board fails), the second redundancy motor controller controls the second power motor stator winding to increase the power output, and the motor stator windings controlled by the other motor drive boards still normally output power.

[0070] If the first stator winding fails (for example, the stator winding of any one of the power motor, the variable pitch motor or the heat dissipation motor), the second power motor driving board in the second redundant motor controller continues to drive the second power motor stator winding to increase the power output, compensating for the partial power loss caused by the failure of the first power motor stator winding, thereby driving the propeller to operate and providing pull or lift for the aircraft; or, the second redundant motor controller controls the second variable pitch motor stator winding to increase the power output, compensating for the partial power loss caused by the failure of the first variable pitch motor stator winding, thereby driving the propeller blade angle to change; or, the second redundant motor controller controls the second heat dissipation motor stator winding to increase the power output, compensating for the partial power loss caused by the failure of the first heat dissipation motor stator winding, thereby driving the circulating pump to rotate to provide liquid circulating pressure to make the cooling liquid flow in the cooling liquid flow channel, or driving the fan to rotate to provide heat dissipation wind speed for the radiator.

[0071] Further, in some embodiments, the heat generating part in the motor controller is integrated with the cooling plate, and / or the heat generating part in the motor controller is arranged in contact with the cooling plate.

[0072] In an implementation, the power device, such as the power motor inverter module (the power device corresponding to the power motor), the heat dissipation motor inverter module (the power device corresponding to the heat dissipation motor) and / or the variable pitch motor inverter module (the power device corresponding to the variable pitch motor), is indirectly attached to the outer surface of the tube wall of the cooling plate through a heat conductive material.

[0073] In another implementation, the power device, such as the power motor inverter module (the power device corresponding to the power motor), the heat dissipation motor inverter module (the power device corresponding to the heat dissipation motor) and / or the variable pitch motor inverter module (the power device corresponding to the variable pitch motor), is directly mounted on the cooling plate to realize integrated design.

[0074] Optionally, a heat conductive layer, such as heat conductive paste, heat conductive pad, phase change material, heat conductive glue, etc., can be arranged between the power device and the cooling plate to reduce thermal resistance and improve heat transfer efficiency.

[0075] In the embodiments of the present application, the heat generating part of the motor controller is integrated with the cooling plate, which saves space, has more compact structure, has high heat conduction efficiency, reduces the risk of thermal failure, and thus improves the reliability of the system; the heat generating part of the motor controller is arranged in contact with the cooling plate, which is convenient to maintain and has high flexibility, in addition, the contact design can more easily adapt to different cooling requirements, and the heat dissipation performance can be optimized by adjusting the heat conductive interface material and the cooling plate design.

[0076] In the electric motor, the power motor and the motor controller are heat generating devices. The bus capacitor and power devices in the motor controller generate heat during operation. Compared with the power devices in the power motor and the motor controller, the bus capacitor generates less heat, and the cooling system (such as liquid cooling or air cooling) does not actively cool the bus capacitor.

[0077] Therefore, in some embodiments, the heat generating components of the motor controller mainly include power devices of the motor controller, and the heat generating components in the motor controller are cooled by the cooling plate.

[0078] The cooling plate is made of high thermal conductivity metal materials such as aluminum or copper, which can quickly conduct heat and effectively reduce the temperature of the heat generating components. In addition, the surface area of the cooling plate can be increased to improve the heat dissipation efficiency, and the thickness and shape can be designed according to the specific application requirements to balance the heat dissipation performance and space limitations.

[0079] The cooling of the heat generating components in the motor controller by the cooling plate can effectively dissipate heat to prevent the power devices from overheating and maintain the performance stability of the power devices, thereby ensuring the normal power output of the power motor.

[0080] In some embodiments, the heat dissipation motor includes a circulating pump motor, which provides power for the circulating pump, or the circulating pump motor provides power for the circulating pump and the fan respectively, or the heat dissipation motor includes a circulating pump motor and a fan motor.

[0081] In one implementation, the heat dissipation motor includes a circulating pump motor, and the electric motor includes a fan. The circulating pump motor is shared by the circulating pump and the fan, that is, the circulating pump motor provides power for the circulating pump and the fan respectively. For example, the circulating pump motor is in transmission connection with the circulating pump, and the circulating pump motor is also in transmission connection with the fan. The circulating pump motor provides power for the fan to drive the fan blades to rotate, and also provides power for the circulating pump to output a suitable rotating speed to flow and exchange heat of the fluid in the internal passage of the power motor and the motor controller.

[0082] In another implementation, the heat dissipation motor includes a circulating pump motor, which provides power for the circulating pump. That is, the electric motor does not include a fan. It can be understood that other ways can be used to replace the fan to dissipate heat from the radiator, such as heat dissipation fins, physical modules containing heat dissipation materials or heat conduction materials, etc. For example, the physical module is arranged on the surface, inside or any position of the radiator to absorb heat or conduct heat and improve the heat conduction efficiency. The heat conduction materials include heat conduction paste, heat conduction pad and heat conduction glue, etc. The heat dissipation materials include phase change materials, metal matrix composites, etc. The heat dissipation fins are thin sheets attached to the main body of the radiator to increase the surface area and enhance the heat dissipation effect.

[0083] In another implementation, the heat dissipation motor includes a circulating pump motor and a fan motor. That is, the electric motor includes a fan and a circulating pump.

[0084] The heat dissipation motor includes a circulating pump motor and a fan motor, and the electric motor includes a fan. For example, the circulating pump motor is drivingly connected to the circulating pump, and the fan motor is drivingly connected to the fan. The fan motor provides power to the fan to rotate the fan blades, and the circulating pump motor provides power to the circulating pump to output a suitable rotating speed to flow and exchange heat of the fluid in the internal passage of the power motor and the motor controller.

[0085] The design of the fan motor and the circulating pump motor in the same motor can reduce the overall volume and weight of the electric motor, reduce the cost, simplify the design of the electric motor, reduce the maintenance requirement, and also reduce the noise and vibration. The design of the fan motor and the circulating pump motor in different motors has higher flexibility, to a certain extent, ensures the optimization of the performance of the motor, and thus improves the heat dissipation efficiency.

[0086] It should be noted that the suitable implementation can be selected according to the actual requirement and the design requirement, and the embodiments of the present application do not limit this.

[0087] In some embodiments, if the heat dissipation motor includes a circulating pump motor and a fan motor, the circulating pump motor and the fan motor are respectively controlled by the motor controller.

[0088] Correspondingly, the motor controller integrates the control of the circulating pump motor and the fan motor. The motor controller further includes a circulating pump motor driving board, a power device corresponding to the circulating pump motor (a circulating pump motor inverter module), a fan motor driving board, and a power device corresponding to the fan motor (a fan motor inverter module).

[0089] For example, the circulating pump motor and the fan motor are double-stator winding.

[0090] Further, in the first redundancy motor controller, the main control board is connected with the circulating pump motor drive board, the power device driven by the circulating pump motor drive board is connected with the first circulating pump motor stator winding; the main control board is connected with the fan motor drive board, the power device driven by the fan motor drive board is connected with the first fan motor stator winding; in the second redundancy motor controller, the main control board is connected with the circulating pump motor drive board, the power device driven by the circulating pump motor drive board is connected with the second circulating pump motor stator winding; the main control board is connected with the fan motor drive board, the power device driven by the fan motor drive board is connected with the second fan motor stator winding. For example, when the first fan motor stator winding fails, the second fan motor stator winding is controlled to run by the second redundancy motor controller, and the power output is increased to drive the fan to rotate, thereby compensating for the partial power loss caused by the failure of the first fan motor stator winding. When the first circulating pump motor stator winding fails, the second circulating pump motor stator winding is controlled to run by the second redundancy motor controller, and the power output is increased to drive the circulating pump to rotate, thereby compensating for the partial power loss caused by the failure of the first circulating pump motor stator winding.

[0091] In the embodiments of the present application, the fan motor and the circulating pump motor adopt a double-stator winding design, which ensures that even if one stator winding fails, the electric motor can still maintain effective cooling, prevent overheating and power loss, and further ensure the stability and safety of the electric motor, thereby ensuring the safety and stable flight of the aircraft. In addition, the circulating pump motor and the fan motor are controlled by the motor controller, which can provide accurate speed control to ensure that the circulating pump and the fan operate under optimal conditions.

[0092] In some embodiments, the circulating pump motor is arranged adjacent to the radiator, for example, the circulating pump motor is located on the upper side, lower side, left side or right side of the radiator, etc. The radiator can be integrated in the electric motor, or can not be integrated, i.e., not considered as part of the electric motor.

[0093] In the embodiments of the present application, the circulating pump motor is arranged adjacent to the radiator, which optimizes the overall layout of the system and reduces the length of the overall pipeline and connecting pieces of the system. In addition, the arrangement of the circulating pump motor adjacent to the radiator shortens the path of the cooling liquid flowing in the system, thereby reducing the flow resistance of the cooling liquid in the cooling pipeline of the system; or, the arrangement of the circulating pump motor adjacent to the radiator shortens the path of the cooling liquid flowing from the radiator into the circulating pump, thereby reducing the flow resistance of the cooling liquid in the cooling pipeline between the radiator and the circulating pump, thereby reducing the energy consumption of the circulating pump.

[0094] In some embodiments, when the radiator motor includes a circulating pump motor and a fan motor, the circulating pump motor and the fan motor are arranged on the same side or different sides of the radiator.

[0095] For example, the circulation pump motor and the fan motor are respectively located on the upper and lower sides, the left and right sides, or the same side of the radiator. Alternatively, to maximize the balance of the aircraft or the compactness of the limited space, the circulation pump motor and the fan motor can be arranged on the upper and lower sides of the radiator.

[0096] It should be noted that the position of the circulation pump motor and / or the fan motor is not specifically limited in the embodiments of the present application.

[0097] In the embodiments of the present application, the circulation pump motor and the fan motor are arranged on the same side or different sides of the radiator, which optimizes the overall layout of the system and reduces the length of the overall pipeline and connecting piece of the system. In addition, arranging the circulation pump motor and the fan motor on different sides of the radiator can further promote more uniform heat distribution and improve heat dissipation. Arranging the circulation pump motor and the fan motor on different sides can also reduce airflow interference between the fan and the circulation pump and optimize the performance of each.

[0098] Figure 2 The structure schematic diagram of the motor controller provided for the exemplary embodiments of the present application is shown. The motor controller includes a bus capacitor, a control module, and a cooling plate, wherein the control module is mainly composed of a PCBA component, and the control module includes a main control board, a power motor driving board, a variable pitch motor driving board, a pump motor driving board, and corresponding power devices, and the power devices include an inverter module. As shown in Figure 3 , the motor controller is a dual-redundancy design, mainly composed of a first bus capacitor 211, a second bus capacitor 212, a first cooling plate 221, a second cooling plate 222, a first inverter module 231, a second inverter module 232, a first motor driving board 241, a second motor driving board 242, a first main control board 251, and a second main control board 252.

[0099] Figure 2 The structure schematic diagram of the electric motor provided for the exemplary embodiments of the present application is shown Figure 3 . The motor controller is a dual-redundancy design, and each motor controller can include a control printed circuit board assembly (PCBA), a gate driving board (PCBA), an inverter module (PCBA), a capacitor module, a controller shell, a heat dissipation channel, and various mounting components, wherein the control printed circuit board assembly corresponds to the electronic control module in Figure 3 , the gate driving board corresponds to the power motor driving module, the variable pitch motor driving module, the circulation pump motor driving module, and the fan motor driving module in Figure 3 , and the inverter module corresponds to the power motor inverter module, the variable pitch motor inverter module, the circulation pump motor inverter module, and the fan motor inverter module in Figure 4 .

[0100] The control printed circuit board assembly (PCBA) can monitor various sensors and / or control various accessory units or brakes based on sensor feedback, and is connected to a flight control system through a communication bus, such as a CAN bus, an RS485 bus, etc., and the flight control system issues flight computer instructions, and the control printed circuit board assembly is preferably a printed circuit board (PCB).

[0101] The gate drive board (PCBA) can include a PWM drive circuit, an overcurrent, overvoltage, undervoltage, and temperature protection circuit, a voltage supply circuit, and a bus voltage acquisition circuit.

[0102] The inverter module (PCBA) can include an inverter bus for high current and low inductance, and the inverter module can also include a sensor assembly. Possible sensors can include sensors for current shunt, motor temperature, and power semiconductor module temperature.

[0103] The motor controller's power motor inverter module, pitch motor inverter module, circulating pump motor inverter module, and fan motor inverter module provide three-phase current to drive the corresponding power motor, pitch motor, pump motor, and fan motor to rotate through three-phase cables or copper bars (U-phase, V-phase, W-phase), wherein the power motor, pitch motor, and circulating pump motor are designed with double-stator windings.

[0104] As shown in Figure 4 The gate drive board is composed of power motor drive module A, power motor drive module B, pitch motor drive module A, pitch motor drive module B, circulating pump motor drive module A, circulating pump motor drive module B, fan motor drive module A, fan motor drive module B, and supporting components, etc.

[0105] The power motor drive module A and the power motor drive module B provide power to the power motor winding A and the power motor winding B, respectively. The pitch motor drive module A and the pitch motor drive module B provide power to the pitch motor winding A and the pitch motor winding B, respectively. The circulating pump motor drive module A and the circulating pump motor drive module B provide power to the pump motor winding A and the pump motor winding B, respectively. The fan motor drive module A and the fan motor drive module B provide power to the fan motor winding A and the fan motor winding B, respectively.

[0106] Next, the following is described from the perspective of integrated optimization arrangement design of the electric motor.

[0107] In some embodiments, the motor controller, the circulating pump motor, the radiator, and the fan motor are coaxially arranged in sequence along the rotation axis direction of the power motor.

[0108] It can be understood that the circular components such as the circulation pump motor, the fan motor, the radiator and the motor controller are all concentric with the rotation axis of the power motor and are compactly distributed axially along a common axis.

[0109] Optionally, the variable pitch motor is coaxial with the rotation axis of the power motor, and the variable pitch motor, motor controller, circulating pump motor, radiator and fan motor are arranged axially along the rotation axis of the power motor in sequence, making the overall design more compact and space utilization high, while reducing the cable length between components and simplifying wiring and connection; in addition, setting the variable pitch motor axially along the rotation axis of the power motor can make the motor controller closer to the variable pitch motor, improve the control response speed and accuracy, and achieve optimized control, which is particularly suitable for aircraft applications that require efficient, compact and reliable operation.

[0110] In some embodiments, adjacent axially arranged parts of the power motor, the motor controller, the circulating pump motor, the fan motor, and the radiator are connected as a whole through structural members.

[0111] For example, Figure 4 A schematic diagram of a cross-sectional layout of an electric engine provided for an exemplary embodiment of the present application is shown in FIG. Figure 4 As shown, all components are arranged along a common central axis (the power motor rotation axis), namely, the variable pitch motor 14, motor controller 11, circulation pump motor 43, radiator 44 and fan motor 45 are axially stacked in sequence and connected as a whole through structural parts (not shown in the figure). The power motor 12 is an outer rotor motor, which is installed and connected to the propeller hub through the rotor housing 46 to provide rotational power for the propeller. The variable pitch motor 14 provides variable pitch power for the propeller pitch mechanism. The circulation pump motor 43 drives the circulation pump to flow and exchange heat for the fluid in the internal channels of the power motor 12 and the motor controller 11. Figure 5 The variable pitch motor 14, fan motor 45, power motor 12 and circulating pump motor 43 are of double stator winding design, and the motor controller 11 is of double redundancy design.

[0112] It should be noted that ​ As just an example, the location of the power motor on the aircraft may depend on the type of aircraft. For example, for a fixed-wing aircraft, the power motor may be located at the nose, wing or tail; for a helicopter, the power motor may be located at the top or tail of the fuselage; for a hybrid aircraft, fixed-wing power motors are installed on the wings, and motors for vertical take-off and landing are installed on the fuselage; and so on. This application does not limit the specific location of the power motor.

[0113] The axial arrangement of the components can reduce the overall space occupied by the electric motor, making the design more compact and space-efficient, while reducing the length of cables between components, simplifying wiring and connections. In addition, the axial arrangement can bring the motor controller closer to the controlled components (such as the motor), improving control response speed and accuracy, optimizing control, and being particularly suitable for aircraft applications that require efficient, compact and reliable operation.

[0114] In some embodiments, the electric motor interacts with the flight control system, which is used to control the electric motor.

[0115] For example, the electric motor is connected to the flight control system, specifically the main control board of the motor controller in the electric motor can be connected to and communicate with the flight control system, for example, through CAN bus, RS485 bus, Wi-Fi connection, etc.

[0116] The main control board of the motor controller can communicate with the sensor to collect operating parameters such as current, voltage, temperature and speed of the electric motor, as well as fault information, etc., and report the operating parameters and fault information to the central control system or user interface through CAN bus, RS485 bus, Wi-Fi module, etc. The central control system is, for example, the flight control system.

[0117] The electric motor also receives control instructions from the flight control system.

[0118] The electric motor of the embodiments of the present application monitors and reports operating information to the flight control system, providing data support for timely detection and handling of abnormal conditions of the electric motor, optimizing system performance, and improving the reliability and safety of the system, thereby ensuring the stability and reliability of the system in various flight states.

[0119] The above embodiments describe the electric motor, and next, the present application also provides an electric propulsion device, such as ​The schematic diagram of the electric propulsion device structure is provided for the exemplary embodiments of the present application. As shown in FIG. 5, the electric propulsion device 50 comprises a variable pitch propeller 51 and the electric motor 10 described in the above embodiments, wherein the variable pitch propeller 51 comprises a spinner 53, a variable pitch mechanism 54, a propeller 55, a hub 56, and a variable pitch motor 57, the spinner 53 and the propeller 55 are assembled to the hub 56, the hub 56 is internally assembled with the variable pitch mechanism 54 and the variable pitch motor 14, and the bottom of the propeller 55 is connected with the variable pitch mechanism 54. The electric motor 10 comprises a motor controller 11, a cooling structure, a power motor 12, and connecting members and lines. The cooling structure is composed of a first cooling plate 221, a second cooling plate 222, a circulating pump (not marked in the figure), a radiator 44, a fan (not marked in the figure), and a cooling pipeline, etc. The motor controller 11 is composed of a main control board, a power motor driving board, a variable pitch motor driving board, a pump motor driving board, and a fan motor driving board. The circulating pump is a mechanical pump, the circulating pump rotor is driven by a circulating pump motor 43, the fan provides a forced air cooling speed for the radiator 44, and the fan rotor is driven by a fan motor 45. The first cooling plate 221 and the second cooling plate 222 conduct and transfer the heat generated by the power devices of the motor controller, and then the heat is cooled and exchanged by the cooling liquid in the internal cooling liquid flow channel.

[0120] The power motor 12, the variable pitch motor 14, the circulating pump motor 43, and the fan motor 45 are all designed with double-stator winding, which can be an outer rotor or an inner rotor design. The power motor 12 is composed of winding A and winding B, the variable pitch motor 14 is composed of variable pitch motor winding A and variable pitch motor winding B, the circulating pump motor 43 is composed of pump motor winding A and pump motor winding B, and the fan motor 45 is composed of fan motor winding A and fan motor winding B.

[0121] In some embodiments, the variable pitch mechanism adopts a worm and gear structure, or a planetary reduction structure, or a screw structure.

[0122] The worm and gear structure has self-locking ability, can keep the angle of the propeller stable without additional braking devices, has high reduction ratio, and has relatively compact structure, which is suitable for the design environment with limited space.

[0123] The planetary reduction structure provides high efficiency and high torque output, is suitable for applications requiring high power transmission, has symmetrical and compact design, and provides high-precision speed and position control.

[0124] The screw structure provides high-precision linear motion control, is suitable for applications requiring precise variable pitch adjustment, is generally designed to be simple, easy to manufacture and maintain, and can bear relatively high axial load.

[0125] It should be noted that in the design of the variable pitch propeller, according to the specific application requirements, such as space limitations, load requirements, precision requirements and cost considerations, a suitable variable pitch mechanism is selected.

[0126] In some embodiments, the variable pitch propeller further comprises a guide fan assembled to the propeller hub.

[0127] The guide fan can optimize the path of airflow through the propeller, reduce vortex and airflow separation, and thus improve the propulsion efficiency of the propeller; the guide fan helps to guide the airflow and enhances the cooling effect of the fan on the engine or other key components, especially in high load or high temperature environments. In addition, the guide fan can increase additional thrust and improve the overall power performance of the system.

[0128] The application also provides an aircraft, comprising: an aircraft body and the above-mentioned electric motor; or, the aircraft comprises: an aircraft body and the above-mentioned electric propulsion device.

[0129] The application of the above-mentioned electric motor or electric propulsion device to the aircraft can achieve efficient, stable and safe flight.

[0130] In some embodiments, the aircraft further comprises: a tilting motor for controlling the tilting mechanism.

[0131] For example, the tilting mechanism and the tilting mechanism inverter are arranged in the aircraft arm, the tilting mechanism comprises a tilting motor, and the control of the tilting motor is independent of the electric motor, that is, the electric motor does not integrate the control of the tilting motor.

[0132] In the embodiment of the application, the tilting motor of the tilting mechanism and the control of the tilting motor exist independently outside the electric motor, so that the structure of the electric motor is lighter and more compact. In addition, the independent system design allows greater flexibility, and the configuration of the tilting mechanism can be adjusted according to different aircraft application requirements without affecting the design of the electric motor.

[0133] In summary, the application has at least the following advantages:

[0134] I. The control of the power motor, the cooling motor and / or the variable pitch motor is integrated, the power motor, the cooling motor and / or the variable pitch motor are controlled by the motor controller, the complexity of the cable connection is reduced, the size and weight of the electric motor are reduced, miniaturization and light weight are realized, thereby reducing energy consumption and realizing efficient flight. In addition, the motor controller integrates the control of multiple motors, which can optimize the efficiency of the electric motor system and improve the cruising range of the aircraft.

[0135] II. The motor adopts a double-stator winding design. When one set of motor windings fails, the other set of windings can continue to work, increasing power output. In the event of a failure of one stator winding, the motor can still maintain stable output, thereby ensuring the reliability, stability and safety of the electric motor and the safe and stable flight of the aircraft.

[0136] III. The motor controller adopts a double-redundancy design. When one motor controller fails, the other motor controller continues to work, achieving high-efficiency control and high-redundancy effect, thereby improving the reliability and safety of the electric motor and ensuring the safe and stable operation of the aircraft.

[0137] IV. The heat generated by the power components in the motor controller is dissipated through the cooling plate. Effective heat dissipation can prevent the power components from overheating and maintain their performance stability, thereby reducing the failure rate. The heat generating parts of the power components are integrated with the cooling plate, saving space and making the structure more compact. The heat conduction efficiency is high, reducing the risk of thermal failure and improving the reliability of the system. The heat generating parts of the power components are arranged in close contact with the cooling plate, making maintenance convenient and flexible. In addition, the close design can more easily adapt to different cooling needs by adjusting the thermal interface material and cooling plate design to optimize the heat dissipation performance.

[0138] V. The circulation pump motor and the fan motor are arranged on the same side or different sides of the radiator. The circulation pump motor is arranged near the radiator to optimize the overall layout of the system and reduce the length of the overall pipeline and connecting parts. In addition, arranging the circulation pump motor and the fan motor on different sides of the radiator can further promote more uniform heat distribution and improve heat dissipation. Arranging them on different sides can also reduce airflow interference between the fan and the circulation pump and optimize their respective performance.

[0139] VI. The fan motor and the circulation pump motor adopt a double-stator winding design to ensure that even if one stator winding fails, the electric motor can still maintain effective cooling and prevent the system from overheating, thereby ensuring the stability and safety of the electric motor and the safe and stable flight of the aircraft. In addition, the circulation pump motor and the fan motor are controlled by separate motor controllers, which can provide precise speed control to ensure that the circulation pump and the fan operate under optimal conditions.

[0140] VII. Axial arrangement of the components inside the electric motor can reduce the overall space occupied by the electric motor, making the design more compact and space-efficient. It also reduces the length of the cables between the components, simplifying wiring and connections. In addition, axial arrangement can bring the motor controller closer to the controlled components (such as the motor), improving control response speed and accuracy and achieving optimal control, especially suitable for aircraft applications that require efficient, compact and reliable operation.

[0141] Eight, the tilting motor of the tilting mechanism and the control of the tilting motor exist independently from the electric motor, so that the structure of the electric motor is lighter and more agile, in addition, the independent system design allows greater flexibility, which can adjust the configuration of the tilting mechanism according to different application requirements, without affecting the design of the electric motor.

[0142] It should be understood, however, that the scope of the application is not limited to the specific embodiments illustrated herein, but includes any and all embodiments which come within the scope of the claims. It is therefore contemplated to cover by the present application any and all changes, modifications, variations, or equivalents that fall within the scope of the present application as defined by the appended claims.

Claims

1. An electric motor, characterized in that: include: A motor controller and a power motor, wherein the motor controller is used to control the power motor, and the motor controller is also used to control the heat dissipation motor and / or the variable pitch motor, and the motor controller is a dual-redundancy design.

2. The motorized engine of claim 1, wherein, The power motor, the variable pitch motor and the heat dissipation motor are designed with double stator windings.

3. The motor-generator according to claim 1 or 2, characterized by The heat generating part in the motor controller is integrated with the cooling plate, and / or the heat generating part in the motor controller is arranged in close contact with the cooling plate.

4. The motor generator according to claim 1 or 2, characterized by The heat dissipation motor includes a circulation pump motor, and the circulation pump motor provides power for the circulation pump, or the circulation pump motor provides power for the circulation pump and the fan respectively; Alternatively, the heat dissipation motor includes a circulation pump motor and a fan motor.

5. The motorized engine of claim 4, wherein, The circulating pump motor is arranged adjacent to the radiator.

6. The motorized engine of claim 4, wherein, When the heat dissipation motor includes the circulation pump motor and the fan motor, the circulation pump motor and the fan motor are respectively arranged on the same side or different sides of the radiator.

7. The motorized engine of claim 6, wherein, The motor controller, the circulating pump motor, the radiator and the fan motor are coaxially arranged in sequence along the rotation axis direction of the power motor.

8. The motorized engine of claim 7, wherein, The power motor, the motor controller, the circulating pump motor, the fan motor and the adjacent parts of the radiator that are coaxially arranged are connected into a whole through structural parts.

9. An electric propulsion device, characterized by include: A variable pitch propeller and an electric engine as claimed in any one of claims 1 to 8, wherein the variable pitch propeller comprises a fairing, a pitch changing mechanism, a propeller, a hub and a pitch changing motor, the fairing and the propeller are both assembled on the hub, the pitch changing mechanism and the pitch changing motor are assembled inside the hub, and the bottom of the propeller is connected to the pitch changing mechanism.

10. An aircraft, characterized in that include: An aircraft body and an electric engine according to any one of claims 1 to 8; Alternatively, the aircraft comprises an aircraft body and the electric propulsion device according to claim 9.

11. The aircraft of claim 10, wherein, Also includes: A tilt motor used to control the tilt mechanism.

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