An aircraft electric drive assembly system

Abstract

The application belongs to the technical field of aircrafts, and discloses an aircraft electric drive assembly system. The system comprises a support, an end cover matched with the support, and a motor, a controller, a rotor and a heat dissipation module arranged based on the support. The motor, the controller and the heat dissipation module are integrated by the support to reduce the size of the system; the motor and the controller are commonly cooled by the heat dissipation module, so that the high heat dissipation rate is realized under the condition of reducing the size and volume of the system; the use of additional driving components is avoided by the magnetic driving design of the oil pump, so that the lightweight of the system volume is realized; the lightweight of the system volume is realized by the tilting wing design. As can be seen from the above, the application can simultaneously realize the requirements of smaller size, lighter weight and stronger heat dissipation capacity of the aircraft electric drive assembly system.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to an aircraft electric drive assembly system. Background Technology

[0002] In the existing technology, the electric drive assembly system refers to an integrated electric drive system composed of a motor, controller, and reducer, which is used in electric vehicles. With the gradual rise of the low-altitude industry and the high efficiency advantage of electric generators themselves, low-altitude flight equipment such as drones and electric vertical take-off and landing aircraft are also increasingly inclined to adopt electric drive assembly systems.

[0003] However, low-altitude flight equipment has much stricter requirements in terms of weight and size compared to electric vehicles, making the relatively mature electric drive system in electric vehicles unsuitable for widespread application. Specifically, while electric drive systems offer advantages such as smaller footprint and lighter weight, these are not key performance indicators for electric vehicles. Therefore, electric drive system design primarily focuses on improving power performance, rather than size and heat dissipation. However, in low-altitude flight equipment, such as electric vertical takeoff and landing (EVL) aircraft, the equipment itself needs efficient vertical takeoff and landing capabilities, stable hovering performance, and efficient cruise capabilities, all of which require a lighter electric drive system as structural support. Furthermore, the hovering and vertical takeoff and landing processes of EVL aircraft generate significant heat, requiring excellent heat dissipation performance from the electric drive system to ensure the reliability and safety of the electric motors during these processes. Conversely, the more integrated and lightweight electric drive system presents a direct challenge in terms of heat dissipation.

[0004] In summary, there is an urgent need for an electric drive system for aircraft that can simultaneously meet the requirements of smaller size, lighter weight, and stronger heat dissipation when applied to aircraft. Summary of the Invention

[0005] The purpose of this invention is to provide an electric drive assembly system for aircraft, so as to solve the technical problem that the electric drive assembly systems commonly used in the field of electric vehicles cannot be well applied to aircraft.

[0006] To achieve the above objectives, the present invention proposes the following technical solution:

[0007] This technical solution provides an electric drive assembly system for an aircraft, including: a bracket, an end cap that cooperates with the bracket, and a motor, controller, rotor and heat dissipation module set based on the bracket;

[0008] The bracket is a ring structure, including a first mounting part and a second mounting part; the first mounting part includes a mounting recess, a ring body and a fixing plate, a drive shaft is provided at the center of the mounting recess, an annular groove is provided on the mounting recess, and the fixing plate is fixed to the lower end of the drive shaft; the second mounting part includes a hollow body, which is coaxially arranged with the ring body; wherein, the drive shaft is a hollow shaft, and the fixing plate is used for detachable mounting of the variable pitch motor;

[0009] The end cap is movably mounted on the drive shaft and includes a cover plate, a third mounting part, and a fourth mounting part; the outer periphery of the cover plate is provided with several mounting holes; the third mounting part extends from the lower surface of the cover plate toward one side of the annular groove; the fourth mounting part extends from the unused end of the cover plate toward the annular body in a covering manner; wherein, the third mounting part is provided with a first magnet.

[0010] The rotor is mounted on the cover plate through corresponding mounting holes;

[0011] The motor includes a stator and a rotor; the stator is fixedly sleeved on the annular body, and the rotor is fixed on the inner side wall of the fourth mounting part and spaced apart from the stator;

[0012] The controller includes several circuit boards, each circuit board being located within the second mounting section;

[0013] The heat dissipation module includes: a magnetic pump, a cooling chamber, a cooling coil, an oil cooler, a centrifugal fan, and an air guide shroud; the magnetic pump includes an oil pump and a second magnet, the oil pump is embedded in an annular groove, and the second magnet is attached to the outer periphery of the oil pump and is spaced apart from the first magnet; the cooling chamber is shrouded on the stator and includes a fiber sleeve and several oil baffle rings; wherein, the fiber sleeve is attached to the stator, and the oil baffle rings are fixed to the ends of the fiber sleeve and the corresponding positions of the annular body; the oil cooler is placed in the second mounting part and includes several cooling pipes and several heat dissipation fins, each cooling pipe is coiled in an annular shape, and each heat dissipation fin is sequentially spaced through the cooling pipes; the cooling coil is fixedly mounted on the empty surface of each circuit board, and both the cooling coil and the circuit board are placed inside the oil cooler; the air guide shroud is fixedly attached to the second mounting part; the centrifugal fan is axially fixed to the air guide shroud; wherein, the cooling chamber contains cooling oil, and the oil cooler, oil pump, cooling coil, and cooling chamber are sequentially connected through cooling oil channels to form a closed loop.

[0014] Furthermore, the variable pitch motor includes a main body and a rotating shaft;

[0015] When the rotor is a tilting rotor, the main body is mounted on the fixed plate, and the rotating shaft is inserted into the transmission shaft.

[0016] Furthermore, a plug is included; when the rotor is a fixed wing, the plug is inserted into the drive shaft.

[0017] Furthermore, the drive shaft and the bracket are separate structures, and a circular hole is provided at the center of the mounting recess, through which the drive shaft is fixed; wherein, the drive shaft is a steel shaft, and the bracket is a lightweight alloy bracket.

[0018] Furthermore, the third mounting part and the fourth mounting part are separate structures, the third mounting part is made of lightweight metal, and the fourth mounting part is made of steel.

[0019] Furthermore, the radial dimension of the first mounting part is smaller than the radial dimension of the second mounting part; the second mounting part includes a connecting plate, the two ends of which are respectively fixed to the lower end of the annular body and the upper end of the hollow body.

[0020] Furthermore, it includes several fixed interfaces; each fixed interface is spaced apart at the lower end of the second mounting part, used to fix the electric drive assembly system to the target aircraft.

[0021] Furthermore, the controller includes a housing located between the oil cooler and each circuit board, covering each circuit board.

[0022] Furthermore, a dust cover is provided on the second mounting portion.

[0023] Furthermore, the centrifugal fan includes a control unit for independently controlling the centrifugal fan speed.

[0024] Beneficial effects:

[0025] As can be seen from the above technical solutions, the technical solution of the present invention designs an electric drive assembly system for aircraft, which has a smaller overall size, lighter weight, and higher heat dissipation efficiency to meet the usage requirements of electric drive assembly systems in aircraft.

[0026] From the perspective of reducing overall size, this technical solution designs a novel assembly structure. First, a ring-shaped bracket is designed to house the various components, achieving a compact overall structure and reducing overall size. Second, during the installation of each component, to avoid internal layout chaos that could cause interference during subsequent operation and to facilitate functional implementation, the bracket is designed for partitioned installation of each component. Specifically, for the motor, the bracket includes a first mounting part, and based on the ring design of the armature itself, the first mounting part includes a ring-shaped main body, enabling convenient sleeve installation of the armature and reducing the number of parts used. For the heat dissipation module, the bracket includes a second mounting part and a mounting recess in the first mounting part. Since the second mounting part is located below the ring-shaped main body and the mounting recess is located above the ring-shaped main body, during the cooling process, cooling oil flows sequentially through the motor and controller, then is pumped into the oil cooler for heat dissipation, thus achieving integrated heat dissipation for the motor and controller and reducing the number of heat dissipation components. Meanwhile, the controller is placed in the second mounting section and located in the inner ring of the oil cooler, which not only achieves hardware isolation between it and the motor, but also improves the space utilization of the second mounting section. In addition, considering the application of various rotors, space is reserved in the first mounting section, and the drive shaft is set as a hollow shaft with a corresponding fixing plate to meet the installation requirements of the variable pitch motor corresponding to the tiltrotor.

[0027] From the perspective of reducing system weight, the motor and controller are centrally deployed and cooled through the same cooling circuit. This not only saves cooling oil channels but also reduces the overall size and weight. The controller is no longer a controller module including a complete controller housing; only the core circuit board structure is retained to reduce weight. In particular, in the oil pump design, a third mounting part is added to the end cover to attach the first magnet. Secondly, the oil pump is embedded in the annular groove of the mounting platform, and a second magnet is set on the outer periphery of the oil pump, with the second magnet and the first magnet spaced apart and opposite. At this time, under the action of the first and second magnets, the oil pump will move synchronously with the rotor in the armature to drive it, thus eliminating the need to add a drive motor to drive the oil pump. Specifically, the drive motor needs to include the controller, armature, and other structures. Therefore, the overall weight and volume of the oil pump using this magnetic drive are reduced by at least half.

[0028] To improve heat dissipation efficiency, firstly, cooling oil is used to cool the main heat-generating units of the assembly system—the controller and armature—to achieve rapid cooling and ensure normal operation of the aircraft. Simultaneously, a cooling chamber is installed for immersion cooling of the armature to further enhance heat dissipation efficiency. Secondly, an annular oil cooler with heat dissipation fins is designed, and the second mounting section corresponding to the heat dissipation fins is designed with a perforated structure to achieve rapid cooling of the heated cooling oil. Thirdly, a centrifugal fan and air guide are also installed to convert passive air cooling into active air cooling. When the centrifugal fan operates, cool air enters the heat dissipation fins through the second mounting section, carrying away heat, and is then quickly discharged through the air guide, reducing the oil temperature.

[0029] In summary, this technical solution, in designing this electric drive assembly system, comprehensively considers size, weight, and heat dissipation requirements. Through a series of improvements, including new structural design and optimized deployment methods, a suitable electric drive assembly system for aircraft has been obtained. Its minimum height can reach 260mm, its lightest weight can reach 52kg, and the highest coil temperature is only 155℃, far less than 180℃.

[0030] It should be understood that all combinations of the foregoing concepts and the additional concepts described in more detail below can be considered part of the inventive subject matter of this disclosure, provided that such concepts do not contradict each other.

[0031] The foregoing and other aspects, embodiments, and features of the teachings of the present invention will be more fully understood from the following description in conjunction with the accompanying drawings. Other additional aspects of the invention, such as features and / or beneficial effects of exemplary embodiments, will become apparent from the following description or may be learned through practice of specific embodiments according to the teachings of the present invention. Attached Figure Description

[0032] The accompanying drawings are not intended to be drawn to scale. In the drawings, each identical or nearly identical component shown in the various figures may be denoted by the same reference numeral. For clarity, not every component is labeled in each figure. Embodiments of various aspects of the invention will now be described by way of example and with reference to the accompanying drawings, wherein:

[0033] Fig. 1 This is a cross-sectional view of the aircraft electric drive assembly system described in this embodiment;

[0034] Fig. 2 This is a schematic diagram of the stator support structure described in this embodiment;

[0035] Fig. 3 This is a schematic diagram of the motor mounting structure described in this embodiment;

[0036] Fig. 4 This is a schematic diagram of the magnetic pump described in this embodiment;

[0037] Fig. 5 This is a schematic diagram of the structure of a portion of the heat dissipation module described in this embodiment.

[0038] The attached diagram is labeled as follows: 1 is the bracket, 2 is the end cover, 3 is the motor, 4 is the controller, 5 is the drive shaft, 6 is the first magnet, 7 is the magnetic pump, 8 is the cooling chamber, 9 is the oil cooler, 10 is the centrifugal fan, 11 is the air guide shroud, 12 is the cooling oil passage, and 13 is the dust cover; 1.1 is the mounting recess, 1.2 is the annular main body, 1.3 is the fixing plate, 1.4 is the hollow main body, 2.1 is the cover plate, 2.2 is the third mounting part, 2.3 is the fourth mounting part, 3.1 is the stator, 3.2 is the rotor, 4.1 is the housing, 7.1 is the oil pump, 7.2 is the second magnet, 8.1 is the fiber sleeve, 8.2 is the oil baffle ring, 9.1 is the cooling pipe, 9.2 is the heat dissipation fins, 10.1 is the control component, 10.2 is the support component, and 10.3 is the fan. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the described embodiments of the present invention without creative effort are within the scope of protection of the present invention. Unless otherwise defined, the technical or scientific terms used herein should have the ordinary meaning understood by those skilled in the art to which this invention pertains.

[0040] The terms "first," "second," and similar words used in this application specification and claims do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Similarly, unless the context clearly indicates otherwise, the singular forms of "an," "a," or "the," etc., do not indicate a quantity limitation, but rather indicate the presence of at least one. Terms such as "comprising" or "including" mean that the element or object preceding "comprising" encompasses the features, wholes, steps, operations, elements, and / or components listed following "comprising" or "including," and do not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or sets thereof. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0041] The low-altitude airspace industry is developing rapidly, and the electric drive system, as the core power source for flight equipment such as UAVs and electric vertical takeoff and landing (EVL) aircraft, is crucial to the performance of these devices. Specifically, taking EVL aircraft as an example, they require efficient vertical takeoff and landing capabilities, stable hovering performance, and efficient cruise capabilities, thus placing demands on the electric drive system for lightweight design, high power density, and high efficiency. Simultaneously, the motors generate significant heat during hovering and vertical takeoff and landing, and the heat generated by the controller during operation can also have adverse effects, necessitating a more efficient cooling system. However, existing electric drive systems cannot adequately address these issues. Therefore, this embodiment aims to provide an electric drive system suitable for aircraft, simultaneously meeting the aforementioned technical requirements of electric drive systems in aircraft.

[0042] The aircraft electric drive assembly system described in this embodiment will be described in detail below with reference to the accompanying drawings.

[0043] like Figs. 1-5 As shown, the assembly system includes a bracket 1, an end cover 2, a motor 3, a controller 4, a rotor, and a heat dissipation module. The end cover 2 cooperates with the bracket 1 to realize the installation and transmission of the rotor; the motor 3, controller 4, rotor, and heat dissipation module are all mounted on the bracket 1.

[0044] In terms of specific structure, the bracket 1 is a ring structure, including a first mounting part and a second mounting part. The first mounting part includes a mounting recess 1.1, a ring-shaped body 1.2, and a fixing plate 1.3. A drive shaft 5 is located at the center of the mounting recess 1.1, and an annular groove 1.1a is provided on the mounting recess 1.1. The fixing plate is fixed to the lower end of the drive shaft 5. The second mounting part includes a hollow body 1.4, which is coaxially arranged with the ring-shaped body 1.2. The drive shaft 5 is a hollow shaft, and the fixing plate 1.3 is used for detachable mounting of the variable pitch motor.

[0045] The end cover 2 is movably mounted on the drive shaft 5 and includes a cover plate 2.1, a third mounting part 2.2, and a fourth mounting part 2.3. The cover plate 2.1 has several mounting holes on its outer periphery. The third mounting part 2.2 extends from the lower surface of the cover plate 2.1 toward one side of the annular groove 1.1a. The fourth mounting part 2.3 extends from the unused end of the cover plate 2.1 toward the annular body in a covering manner. The third mounting part 2.2 is provided with a first magnet 6. In this embodiment, the fourth mounting part 2.3 forms the rotor housing in the motor.

[0046] The rotor is mounted on the cover plate 2.1 through the corresponding mounting holes.

[0047] The motor 3 includes a stator 3.1 and a rotor 3.2. The stator 3.1 is fixedly sleeved on the annular body 1.2, and the rotor 3.2 is fixed on the inner side wall of the fourth mounting part 2.3 and is spaced apart from the stator.

[0048] The controller 4 includes several circuit boards, each located within the second mounting section.

[0049] The heat dissipation module includes: a magnetic pump 7, a cooling chamber 8, a cooling coil, an oil cooler 9, a centrifugal fan 10, and an air guide shroud 11.

[0050] Specifically, the magnetic pump 7 includes an oil pump 7.1 and a second magnet 7.2. The oil pump 7.1 is embedded in the annular groove 1.1a, and the second magnet 7.2 is attached to the outer periphery of the oil pump 7.1 and is spaced apart from the first magnet 6. The cooling chamber 8 is covered on the stator 3.1 and is used for immersion cooling of the stator 3.1 of the motor. It includes a fiber sleeve 8.1 and several oil baffle rings 8.2. The fiber sleeve 8.1 is attached to the stator 3.1, and the oil baffle rings 8.2 are fixed to the ends of the fiber sleeve 8.1 and the corresponding positions of the annular body 1.2.

[0051] The oil cooler 9 is located within the second mounting section and includes several cooling pipes 9.1 and several heat dissipation fins 9.2. Each cooling pipe 9.1 is coiled in a ring, and each heat dissipation fin 9.2 is sequentially spaced through the cooling pipe 9.1. The cooling coil is fixedly mounted on the empty surface of each circuit board, and both the cooling coil and the circuit board are located inside the oil cooler 9. The air guide shroud 11 is fixed to the lower part of the second mounting section, and the centrifugal fan 10 is axially inserted and fixed to the air guide shroud 11. The cooling chamber 8 contains cooling oil, and the oil cooler 9, oil pump 7.1, cooling coil, and cooling chamber 8 are sequentially connected through cooling oil channels 12 to form a closed loop.

[0052] In practical implementation, this embodiment designs a ring-shaped bracket 1, and based on the bracket 1, it simultaneously realizes the centralized installation of various components in the motor 3, controller 4, rotating shaft 6, and heat dissipation module. At this time, the bracket 1 not only achieves a compact layout and miniaturized design of the assembly system, but also achieves the structural regularity of the entire assembly system, making it easy to fix the entire assembly system to the target aircraft.

[0053] In one specific implementation, the radial dimension of the first mounting part is smaller than the radial dimension of the second mounting part; the second mounting part includes a connecting plate, the two ends of which are respectively fixed to the lower end of the annular body 1.2 and the upper end of the hollow body 1.4. In this case, when the motor is installed on the first mounting part, the outer periphery of the entire assembly system will form a regular cylindrical structure, which not only facilitates installation but also helps improve the stability of the structure during high-speed rotation.

[0054] In one specific implementation, the bracket is provided with several fixing interfaces; each fixing interface is spaced apart at the lower end of the second mounting part, and is used to fix the electric drive assembly system to the target aircraft. In this embodiment, the target aircraft can be a drone or an eVTOL.

[0055] In the specific deployment design process, a compact layout was adopted as the foundation, while also considering partitioned layout to avoid mutual interference and assist in realizing corresponding functions. This resulted in the optimization of the overall system size, weight, ease of installation, and operational stability. For example, to facilitate the installation of motor 3, based on the ring design of the armature itself, a first mounting part including a ring-shaped main body 1.2 was set up, thereby enabling convenient sleeve installation of the armature and reducing the number of parts used. For the heat dissipation module, the cooling oil flows sequentially through motor 3 and controller 4, and is then pumped into oil cooler 9 by oil pump 7.1 for heat dissipation, thereby achieving integrated heat dissipation for motor 3 and controller 4 and reducing the number of heat dissipation components. The controller 4 is placed in the second mounting part, located in the inner ring of oil cooler 9, which not only achieves hardware isolation between it and motor 3, but also improves the space utilization of the second mounting part. Furthermore, considering the application of various rotors, space was reserved in the first mounting part, and the drive shaft 5 was set as a hollow shaft, with a corresponding fixing plate 1.3, to meet the installation requirements of the variable pitch motor corresponding to the tilting rotor. The hollow shaft also helps to reduce weight.

[0056] In one specific implementation, the variable-pitch motor includes a main body and a rotating shaft. When the rotor is a tilting rotor, the main body is mounted on the fixed plate 1.3, and the rotating shaft passes through the drive shaft 5. When the rotor is a fixed rotor, a plug is provided and inserted into the drive shaft 5. In this way, not only is the installation of tilting and fixed rotors differentiated, but also, in practical applications, the rotating shaft and plug prevent external impurities from entering the assembly system through the hollow shaft, thus avoiding adverse effects.

[0057] Meanwhile, only the core circuit board structure is retained on the controller 4 to reduce weight. Specifically, in order to achieve hardware isolation between the controller 4 and the heat dissipation module to avoid adverse effects of the external environment on the controller 4, the controller 4 includes a housing 4.1, which is located between the oil cooler 9 and each circuit board and covers each circuit board.

[0058] In the oil pump design, a first magnet 6 and a second magnet 7.2 are installed that interact with the rotor 3.2. Under the action of the first magnet 6 and the second magnet 7.2, the oil pump 7.1 will move synchronously with the rotor 3.2 in the armature to drive it, thus eliminating the need for an additional drive motor for the oil pump. This reduces the size and volume of the assembly system by at least half.

[0059] In a preferred embodiment, to further reduce the overall weight, the drive shaft 5 and the bracket 1 are designed as separate structures. A circular hole is provided at the center of the mounting recess 1.1, and the drive shaft 5 is inserted and fixed within the circular hole. Specifically, the drive shaft is a steel shaft, and the bracket is a lightweight alloy bracket. In this case, the steel shaft ensures structural strength, while the lightweight alloy bracket helps reduce the overall weight of the assembly system. Specifically, the lightweight alloy bracket can be a titanium alloy bracket or an aluminum alloy bracket.

[0060] Similarly, the third mounting part 2.2 and the fourth mounting part 2.3 are configured as separate structures. The third mounting part 2.2 is made of lightweight metal, and the fourth mounting part 2.3 is made of steel. In this case, the steel fourth mounting part 2.3 ensures structural strength, while the lightweight metal third mounting part 2.2 helps reduce the overall system weight. Specifically, the lightweight metal can be titanium alloy or aluminum alloy.

[0061] During the heat dissipation process, firstly, the cooling oil flows through the cooling chamber 8 and the cooling coil in sequence to perform immersion cooling of the armature and dynamic cooling of the components on the circuit board. Then, the heated cooling oil enters the oil cooler 9 under the action of the magnetically driven oil pump 7.1. External cold air is blown quickly from the hollow body 1.4 to the heat dissipation fins 9.2 by the action of the centrifugal fan to quickly remove the heat of the cooling oil in the cooling pipe 9.1. The heated hot air will leave quickly under the action of the air guide shroud 11, thereby achieving rapid heat dissipation.

[0062] As a specific implementation, a dust cover 13 is also provided to prevent external impurities from entering the assembly system during heat dissipation. Specifically, the dust cover 13 is placed on the second mounting part, i.e., the hollow body 1.4. Specifically, the dust cover 13 is fixed to the second mounting part, and the air guide shroud 11 is fixed to the lower end face of the dust cover 13 by screws.

[0063] In a preferred embodiment, to further improve heat dissipation efficiency, the centrifugal fan 10 includes a control component 10.1 for independently controlling the speed of the centrifugal fan 10. Specifically, the centrifugal fan also includes a support component 10.2 and fans 10.3. The support component 10.2 is inserted into the air guide shroud 11 and fixed to the housing 4.1 of the controller 4 to improve structural reliability. The control component 10.1 is positioned at the center of the support component 10.2, and the fans 10.3 are spaced apart along the outer periphery of the controller 10.1. In this case, the speed of the centrifugal fan 10 can be adjusted according to specific needs to regulate the airflow and achieve the goal of improving heat dissipation efficiency.

[0064] In summary, this embodiment presents a novel oil-cooled electric drive assembly system. Through innovative design optimizations such as optimized structural deployment, an integrated oil-cooling combined with air-cooling system, improved oil pump structure, and a new oil cooler design, the system meets the performance requirements for aircraft electric drive assemblies. The assembly system described in this embodiment has a height range of no more than 300mm, with a minimum of 260mm; a weight range of no more than 55kg, with a minimum of 52kg; and a coil temperature during heat dissipation that is significantly lower than 180℃, with a minimum of 155℃.

[0065] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Those skilled in the art can make various modifications and refinements without departing from the spirit and scope of the invention. Therefore, the scope of protection of the present invention shall be determined by the claims.

Claims

1. An aircraft electric drive assembly system, characterized in that, include: The bracket, the end cap that mates with the bracket, and the motor, controller, rotor and heat dissipation module set on the bracket; The bracket is a ring structure, including a first mounting part and a second mounting part; the first mounting part includes a mounting recess, a ring body and a fixing plate, a drive shaft is provided at the center of the mounting recess, an annular groove is provided on the mounting recess, and the fixing plate is fixed to the lower end of the drive shaft; the second mounting part includes a hollow body, which is coaxially arranged with the ring body; wherein, the drive shaft is a hollow shaft, and the fixing plate is used for detachable mounting of the variable pitch motor; The end cap is movably mounted on the drive shaft and includes a cover plate, a third mounting part, and a fourth mounting part; the outer periphery of the cover plate is provided with several mounting holes; the third mounting part extends from the lower surface of the cover plate toward one side of the annular groove; the fourth mounting part extends from the unused end of the cover plate toward the annular body in a covering manner; wherein, the third mounting part is provided with a first magnet. The rotor is mounted on the cover plate through corresponding mounting holes; The motor includes a stator and a rotor; the stator is fixedly sleeved on the annular body, and the rotor is fixed on the inner side wall of the fourth mounting part and spaced apart from the stator; The controller includes several circuit boards, each circuit board being located within the second mounting section; The heat dissipation module includes: a magnetic pump, a cooling chamber, a cooling coil, an oil cooler, a centrifugal fan, and an air guide shroud; the magnetic pump includes an oil pump and a second magnet, the oil pump is embedded in an annular groove, and the second magnet is attached to the outer periphery of the oil pump and is spaced apart from the first magnet; the cooling chamber is shrouded on the stator and includes a fiber sleeve and several oil baffle rings; wherein, the fiber sleeve is attached to the stator, and the oil baffle rings are fixed to the ends of the fiber sleeve and the corresponding positions of the annular body; the oil cooler is placed in the second mounting part and includes several cooling pipes and several heat dissipation fins, each cooling pipe is coiled in an annular shape, and each heat dissipation fin is sequentially spaced through the cooling pipes; the cooling coil is fixedly mounted on the empty surface of each circuit board, and both the cooling coil and the circuit board are placed inside the oil cooler; the air guide shroud is fixedly attached to the second mounting part; the centrifugal fan is axially fixed to the air guide shroud; wherein, the cooling chamber contains cooling oil, and the oil cooler, oil pump, cooling coil, and cooling chamber are sequentially connected through cooling oil channels to form a closed loop.

2. The aircraft electric drive assembly system according to claim 1, characterized in that, The variable pitch motor includes a main body and a rotating shaft; When the rotor is a tilting rotor, the main body is mounted on the fixed plate, and the rotating shaft is inserted into the transmission shaft.

3. The aircraft electric drive assembly system according to claim 1, characterized in that, Includes a plug; when the rotor is a fixed wing, the plug is inserted into the drive shaft.

4. The aircraft electric drive assembly system according to claim 1, characterized in that, The drive shaft and the bracket are separate structures. A circular hole is provided at the center of the mounting recess, and the drive shaft is inserted and fixed in the circular hole. The drive shaft is a steel shaft, and the bracket is a lightweight alloy bracket.

5. The aircraft electric drive assembly system according to claim 1, characterized in that, The third mounting part and the fourth mounting part are separate structures. The third mounting part is made of lightweight metal, and the fourth mounting part is made of steel.

6. The aircraft electric drive assembly system according to claim 1, characterized in that, The radial dimension of the first mounting part is smaller than that of the second mounting part; the second mounting part includes a connecting plate, the two ends of which are respectively fixed to the lower end of the annular body and the upper end of the hollow body.

7. The aircraft electric drive assembly system according to claim 1, characterized in that, It includes several fixed interfaces; each fixed interface is spaced apart at the lower end of the second mounting part, and is used to fix the electric drive assembly system to the target aircraft.

8. The aircraft electric drive assembly system according to claim 1, characterized in that, The controller includes a housing located between the oil cooler and each circuit board, covering each circuit board.

9. The aircraft electric drive assembly system according to claim 1, characterized in that, Includes a dust cover, which is mounted on the second mounting portion.

10. The aircraft electric drive assembly system according to claim 1, characterized in that, The centrifugal fan includes a control unit for independently controlling the centrifugal fan speed.

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