Aircraft electric drive assembly system

Abstract

The invention belongs to the technical field of aircrafts, and discloses an aircraft electric drive assembly system. The system comprises a bracket, an end cover matched with the bracket, and a motor, a controller, a rotor wing and a heat dissipation module which are arranged based on the bracket. Wherein the integrated design of the motor, the controller and the heat dissipation module is realized through the bracket so as to reduce the size of the system; common cooling of the motor and the controller is achieved through the heat dissipation module, and the high heat dissipation rate is achieved under the condition that the size and the volume of the system are reduced; due to the magnetic driving design of the oil pump, the use of additional driving parts is avoided, and the light weight of the system volume is realized; and the lightweight of the system volume is realized through the design of the tilting wings. In conclusion, the requirements of smaller size, lighter weight and stronger heat dissipation capability of the electric drive assembly system of the aircraft can be met at the same time.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft electric drive assembly system. Background Art

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

[0003] However, due to the more stringent weight and volume requirements for low-altitude flight equipment compared to electric vehicles, the relatively mature electric drive systems used in electric vehicles are not well-suited. Specifically, while electric drive systems offer the advantages of a small footprint and lightweight design, these are not key performance indicators for electric vehicles. Therefore, the design of electric drive systems is still primarily focused on improving power performance, with size and heat dissipation not being a core design objective. However, low-altitude flight equipment, such as electric vertical take-off and landing (EVs), requires efficient VTOL capabilities, stable hovering performance, and efficient cruising capabilities, all of which require a more lightweight EV drive system as a level structural support. Furthermore, significant heat is generated during the hovering and vertical take-off and landing phases of EVs. To ensure the reliability and safety of the motors during these processes, the EV drive system must possess excellent heat dissipation performance. Conversely, the more integrated and lightweight EV drive systems present a direct challenge: increased heat dissipation.

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

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

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

[0007] This technical solution provides an aircraft electric drive assembly system, including: a bracket, an end cover matched with the bracket, a motor, a controller, a rotor and a heat dissipation module arranged based on the bracket;

[0008] The bracket is an annular structure, including a first mounting portion and a second mounting portion; the first mounting portion includes a mounting recess, an annular body, and a fixing plate; a transmission 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 transmission shaft; the second mounting portion includes a hollow body, which is coaxially arranged with the annular body; wherein the transmission shaft is a hollow shaft, and the fixing plate is used for detachably mounting the variable pitch motor;

[0009] The end cover is movably mounted on the transmission shaft and includes a cover plate, a third mounting portion, and a fourth mounting portion. A plurality of mounting holes are formed on the outer periphery of the cover plate. The third mounting portion extends from the lower surface of the cover plate toward one side of the annular groove. The fourth mounting portion extends from the free end surface of the cover plate toward the annular body in a covering manner. The third mounting portion is provided with a first magnetic steel.

[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 main body, and the rotor is fixed on the inner side wall of the fourth mounting portion and spaced apart from the stator;

[0012] The controller includes a plurality of circuit boards, each of which is located in the second mounting portion;

[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 cover; the magnetic pump includes an oil pump and a second magnet, the oil pump is embedded in the annular groove, the second magnet is attached to the outer circumference of the oil pump, and is arranged opposite to the first magnet at intervals; the cooling chamber cover is arranged on the stator, including a fiber sleeve and a plurality of oil deflector rings; wherein the fiber sleeve is attached to the stator, and the oil deflector ring is fixed to the corresponding position of the end of the fiber sleeve and the annular main body; the oil cooler is placed in the second mounting part, including a plurality of cooling tubes and a plurality of heat dissipation fins, each cooling tube is arranged in an annular coil, and each heat dissipation fin is sequentially passed through the cooling tube; the cooling coil is fixedly mounted on the spare surface of each circuit board, and is placed on the inner side of the oil cooler together with each circuit board; the air guide cover is fixed to the bottom of the second mounting part; the centrifugal fan is axially passed through and fixed on the air guide cover; 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 tilt rotor, the main body is mounted on the fixing plate, and the rotating shaft is passed through the transmission shaft.

[0016] Furthermore, it includes a plug; when the rotor is a fixed wing, the plug is inserted into the transmission shaft.

[0017] Furthermore, the transmission shaft and the bracket are separate structures, a circular hole is opened at the center of the mounting recess, and the transmission shaft is passed through and fixed in the circular hole; wherein, the transmission shaft is a steel shaft, and the bracket is a light alloy bracket.

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

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

[0020] Furthermore, it includes a plurality of fixing interfaces; each fixing interface is spaced apart and opened at the lower end of the second mounting portion, and is used to fix the electric drive assembly system on the target aircraft.

[0021] Furthermore, the controller includes a shell, which is located between the oil cooler and each circuit board and covers each circuit board.

[0022] Furthermore, it includes a dust cover, which is arranged on the second mounting portion.

[0023] Furthermore, the centrifugal fan includes a control component, and the control component is used to independently control the rotation speed of the centrifugal fan.

[0024] Beneficial effects:

[0025] It can be seen from the above technical solutions that 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 use requirements of the electric drive assembly system in the aircraft.

[0026] To reduce overall size, this technical solution employs a novel assembly structure. First, a ring-shaped bracket is designed to mount the various components, thereby achieving a compact overall structure and reducing overall size. Second, during the installation process, to prevent interference during subsequent operation caused by a chaotic internal layout during compact installation and to facilitate the implementation of corresponding functions, the bracket is designed to allow for partitioned installation of the various components. Specifically, for the motor, the bracket includes a first mounting portion, which, based on the annular design of the armature, includes an annular body. This allows for convenient, sleeved installation of the armature and reduces the number of parts. For the heat dissipation module, the bracket includes a second mounting portion and a mounting recess within the first mounting portion. Since the second mounting portion is located below the annular body and the mounting recess is located above it, during the cooling process, cooling oil flows sequentially through the motor and controller, then is pumped into the oil cooler by an oil pump for heat dissipation. This achieves integrated heat dissipation for the motor and controller, reducing the number of heat dissipation components. The controller is placed within the second mounting section, located on the inner ring of the oil cooler. This not only provides hardware isolation between it and the motor, but also improves the space utilization of the second mounting section. Furthermore, considering the diverse applications of rotors, space is reserved within the first mounting section, and the drive shaft is designed as a hollow shaft with a corresponding fixing plate to accommodate the variable pitch motor required for the tilt-rotor rotor.

[0027] From the perspective of reducing the deadweight of the system, the motor and controller are centrally deployed and cooled through the same cooling circuit. This not only helps to save cooling oil channels, but also helps to reduce weight while reducing the overall volume. The controller is no longer set as a controller module including a complete controller housing. Only the core circuit board structure is retained to reduce weight. In particular, in the design of the oil pump, a third mounting portion is added to the end cover to achieve the attachment of the first magnet; secondly, the oil pump is embedded in the annular groove of the mounting recess, and a second magnet is set on the outer periphery of the oil pump, and the second magnet is arranged relative to the first magnet. At this time, under the action of the first magnet and the second magnet, the oil pump will move synchronously with the rotor in the armature to drive it, so there is no need to add a drive motor to drive the oil pump. Specifically, the drive motor needs to include structures such as a controller and an armature. Therefore, the overall deadweight and volume of the oil pump driven by this magnetic force are reduced by at least half.

[0028] From the perspective of improving heat dissipation efficiency, first, cooling oil is used to cool the main heat-generating units of the assembly system - the controller and the armature, so as to achieve rapid cooling of both and realize the normal operation of the aircraft. At the same time, a cooling chamber is provided to immerse the armature in heat dissipation to improve the heat dissipation efficiency. Secondly, an oil cooler with an annular structure including heat dissipation fins is designed, and the second mounting portion corresponding to the heat dissipation fins is set as a hollow structure to achieve rapid cooling of the heated cooling oil. Furthermore, a centrifugal fan and an air guide cover are also provided to convert passive air cooling into active air cooling. At this time, the centrifugal fan is running, and the cold air enters the heat dissipation fins through the second mounting portion to take away the heat, and is quickly discharged through the air guide cover to reduce the oil temperature.

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

[0030] It should be appreciated that all combinations of the foregoing concepts, as well as additional concepts described in greater detail below, to the extent such concepts are not mutually inconsistent, can be considered to be part of the inventive subject matter of this disclosure.

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

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

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

[0034] Figure 2 Schematic diagram of the structure of the stator bracket according to this embodiment;

[0035] Figure 3 Schematic diagram of the installation structure of the motor described in this embodiment;

[0036] Figure 4 Schematic diagram of the structure of the magnetic pump described in this embodiment;

[0037] Figure 5 This is a schematic structural diagram of part of the heat dissipation module described in this embodiment.

[0038] The reference numerals in the figure are: 1 is the bracket, 2 is the end cover, 3 is the motor, 4 is the controller, 5 is the transmission 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 wind guide cover, 12 is the cooling oil channel, 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 retaining ring, 9.1 is the cooling pipe, 9.2 is the heat dissipation fin, 10.1 is the control part, 10.2 is the support part, and 10.3 is the fan. DETAILED DESCRIPTION

[0039] In order to make the purpose, 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 in conjunction with the drawings of the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the described embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Unless otherwise defined, the technical terms or scientific terms used herein should be the common meanings understood by people with ordinary skills in the field to which the present invention belongs.

[0040] The words “first”, “second” and similar terms used in the specification and claims of this application do not indicate any order, quantity or importance, but are only used to distinguish different components. Similarly, unless the context clearly indicates otherwise, the singular forms of “a”, “an” or “the” and similar words do not indicate a quantitative limitation, but rather indicate the presence of at least one. Words such as “include” or “comprise” mean that the elements or objects appearing before “include” or “comprises” cover the features, wholes, steps, operations, elements and / or components listed after “include” or “comprises”, and do not exclude the existence or addition of one or more other features, wholes, steps, operations, elements, components and / or their collections. “Up”, “down”, “left”, “right” and the like are only used 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 industry is developing rapidly, and the electric drive assembly system, as the core power source for flight equipment such as drones and electric vertical take-off and landing aircraft, is crucial to the performance of the equipment. Specifically, taking the electric vertical take-off and landing aircraft as an example, it is necessary to have efficient vertical take-off and landing capabilities, stable hovering performance, and efficient cruising capabilities, which puts forward requirements for lightweight, high power density and high efficiency for the electric drive assembly system. At the same time, since the motor will generate a lot of heat during hovering and vertical take-off and landing, the heat generated by the controller during operation will also cause adverse effects, so a more efficient cooling system is needed. However, the existing electric drive assembly system cannot solve the above problems well. Based on this, the present embodiment aims to provide an electric drive assembly system suitable for aircraft, so as to simultaneously meet the above technical requirements of the electric drive assembly system in the 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 Figures 1 to 5 As shown, the assembly system includes a bracket 1, an end cap 2, a motor 3, a controller 4, a rotor, and a heat dissipation module. The end cap 2 cooperates with the bracket 1 to achieve the installation and transmission of the rotor; the motor 3, controller 4, rotor, and heat dissipation module are all installed based on the bracket 1.

[0044] Specifically, the bracket 1 is an annular structure, comprising a first mounting portion and a second mounting portion. The first mounting portion comprises a mounting recess 1.1, an annular body 1.2, and a fixing plate 1.3. The drive shaft 5 is positioned at the center of the mounting recess 1.1, which includes an annular groove 1.1a. The fixing plate is secured to the lower end of the drive shaft 5. The second mounting portion comprises a hollow body 1.4, coaxially arranged with the annular body 1.2. The drive shaft 5 is hollow, and the fixing plate 1.3 is used to removably mount the variable pitch motor.

[0045] The end cap 2 is movably mounted on the transmission shaft 5 and comprises a cover plate 2.1, a third mounting portion 2.2, and a fourth mounting portion 2.3. The outer periphery of the cover plate 2.1 is provided with a plurality of mounting holes. The third mounting portion 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 portion 2.3 extends from the free end surface of the cover plate 2.1 toward the annular main body, thereby covering the outer periphery. The third mounting portion 2.2 is provided with a first magnetic steel 6. In this embodiment, the fourth mounting portion 2.3 forms the rotor housing of the motor.

[0046] The rotor is mounted on the cover plate 2.1 through 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 portion 2.3 and spaced apart from the stator.

[0048] The controller 4 includes a plurality of circuit boards, each of which is located in the second mounting portion.

[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 cover 11 .

[0050] Specifically, the magnetic pump 7 comprises an oil pump 7.1 and a second magnetic steel 7.2. The oil pump 7.1 is embedded in the annular groove 1.1a. The second magnetic steel 7.2 is attached to the outer circumference of the oil pump 7.1 and spaced apart from the first magnetic steel 6. A cooling chamber 8 is provided over the stator 3.1 to provide immersion cooling for the motor stator 3.1. The cooling chamber 8 comprises a fiber sleeve 8.1 and several oil deflector rings 8.2. The fiber sleeve 8.1 is attached to the stator 3.1, and the oil deflector 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 housed within the second mounting portion and comprises several cooling tubes 9.1 and several heat dissipating fins 9.2. Each cooling tube 9.1 is arranged in an annular coil, and each heat dissipating fin 9.2 is sequentially spaced and interspersed throughout the cooling tubes 9.1. The cooling coils are fixedly mounted on the free surfaces of each circuit board and, along with the circuit boards, are positioned within the oil cooler 9. An air scoop 11 is secured to the lower portion of the second mounting portion, and a centrifugal fan 10 is axially threaded and secured to the scoop 11. The cooling chamber 8 contains cooling oil. The oil cooler 9, oil pump 7.1, cooling coils, and cooling chamber 8 are interconnected via cooling oil channels 12, forming a closed circuit.

[0052] In practice, this embodiment employs a ring-shaped bracket 1, which simultaneously supports the centralized installation of components including the motor 3, controller 4, rotating shaft 6, and heat dissipation module. This not only allows for a compact layout and miniaturized design of the assembly system, but also ensures a uniform structure for the entire assembly system, facilitating its attachment to the target aircraft.

[0053] In a specific embodiment, the radial dimension of the first mounting portion is smaller than that of the second mounting portion. The second mounting portion includes a connecting plate, the ends of which are respectively secured to the lower end of the annular body 1.2 and the upper end of the hollow body 1.4. When the motor is mounted on the first mounting portion, the outer periphery of the entire assembly forms a regular cylindrical structure, which not only facilitates installation but also improves structural stability during high-speed rotation.

[0054] In a specific embodiment, the bracket is provided with a plurality of fixing interfaces, each of which is spaced apart at the lower end of the second mounting portion and is used to secure the electric drive assembly system to a target aircraft. In this embodiment, the target aircraft can be a drone or an eVTOL.

[0055] During the specific deployment design process, a compact layout was prioritized, while also considering partitioned layouts to avoid mutual interference and facilitate the implementation of corresponding functions. This simultaneously optimized the overall system size, weight, ease of installation, and operational stability. For example, to facilitate the installation of motor 3, based on the annular design of the armature itself, a first mounting portion comprising an annular main body 1.2 was provided. This facilitates the armature's convenient, sleeved installation and reduces the number of parts. Regarding the heat dissipation module, cooling oil flows sequentially through motor 3 and controller 4 before being pumped by oil pump 7.1 into oil cooler 9 for heat dissipation. This achieves integrated heat dissipation for motor 3 and controller 4, reducing the number of heat dissipation components. Controller 4 is placed within the second mounting portion, located on the inner ring of oil cooler 9. This not only provides hardware isolation between it and motor 3, but also improves the space utilization of the second mounting portion. Furthermore, considering the diverse applications of rotors, space was reserved within the first mounting portion, and the drive shaft 5 was designed as a hollow shaft, with a corresponding fixing plate 1.3, to accommodate the installation requirements of the variable pitch motor corresponding to the tilt-rotor rotor. The hollow shaft also contributes to weight reduction.

[0056] As a specific embodiment, the variable pitch motor includes a main body and a rotating shaft. When the rotor is a tilt-rotor, the main body is mounted on the fixed plate 1.3, and the rotating shaft is inserted into the transmission shaft 5. When the rotor is a fixed-wing, a plug is provided and inserted into the transmission shaft 5. This method not only enables the differentiated installation of the tilt-rotor and fixed-wing rotors, but also, in specific applications, prevents external impurities from entering the assembly system through the hollow shaft, potentially causing adverse effects.

[0057] At the same time, 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 prevent adverse effects of the external environment on the controller 4, the controller 4 is configured to include a housing 4.1. The housing 4.1 is located between the oil cooler 9 and the circuit boards and covers the circuit boards.

[0058] The oil pump design incorporates a first magnet 6 and a second magnet 7.2 that interact with the rotor 3.2. Under the action of the first and second magnets 7.2, the oil pump 7.1 moves synchronously with the rotor 3.2 in the armature to drive it, eliminating the need for a separate drive motor for the oil pump. This reduces the size and volume of the overall system by at least half.

[0059] As a preferred embodiment, to further reduce overall weight, the drive shaft 5 and bracket 1 are constructed as separate components. A circular hole is defined at the center of the mounting recess 1.1, into which the drive shaft 5 is inserted and secured. Specifically, the drive shaft is made of steel, and the bracket is made of a lightweight alloy. While the steel shaft ensures structural strength, the lightweight alloy bracket helps reduce the weight of the assembly system. Specifically, the lightweight alloy bracket can be made of either titanium or aluminum alloy.

[0060] Similarly, the third mounting portion 2.2 and the fourth mounting portion 2.3 are separate structures, with the third mounting portion 2.2 constructed of lightweight metal and the fourth mounting portion 2.3 constructed of steel. In this case, the steel fourth mounting portion 2.3 ensures structural strength, while the lightweight metal third mounting portion 2.2 helps reduce the weight of the assembly. Specifically, the lightweight metal can be a titanium alloy or an aluminum alloy.

[0061] During the heat dissipation process, first, the cooling oil will flow through the cooling chamber 8 and the cooling coil in sequence to immerse the armature in heat dissipation and dynamically dissipate heat for the components on the circuit board; then, the heated cooling oil will enter the oil cooler 9 under the action of the magnetically driven oil pump 7.1, and the external cold air will be blown quickly from the hollow body 1.4 to the heat dissipation fins 9.2 under the action of the centrifugal fan to quickly take away the heat of the cooling oil in the cooling tube 9.1, and the heated hot air will quickly leave under the action of the air guide cover 11, thereby achieving rapid heat dissipation.

[0062] In a specific embodiment, a dust cover 13 is provided to prevent external impurities from entering the assembly system during heat dissipation. Specifically, the dust cover 13 is mounted on the second mounting portion, i.e., the hollow body 1.4. Specifically, the dust cover 13 is secured to the second mounting portion, and the air guide 11 is secured to the lower end surface of the dust cover 13 via screws.

[0063] As a preferred embodiment, in order to further improve the heat dissipation efficiency, the centrifugal fan 10 is provided with a control member 10.1, and the control member is used to independently control the rotation speed of the centrifugal fan 10. Specifically, the centrifugal fan also includes a support member 10.2 and a fan 10.3. The support member 10.2 is passed through the air guide cover 11 and is fixed to the housing 4.1 in the controller 4 to improve structural reliability. The control member 10.1 is placed at the center of the support member 10.2, and the fans 10.3 are spaced apart along the periphery of the controller 10.1. At this time, the rotation speed of the centrifugal fan 10 can be adjusted according to specific needs to adjust the wind speed, so as to achieve the purpose of improving the heat dissipation efficiency.

[0064] In summary, this embodiment designs a completely new oil-cooled electric drive assembly system. Through innovative design optimizations such as optimized structural layout, an integrated oil-cooled and air-cooled cooling system, improved oil pump structure, and a novel oil cooler design, it achieves the performance requirements of aircraft electric drive assembly systems. 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 significantly below 180°C during heat dissipation, with a minimum of 155°C.

[0065] While the present invention has been disclosed above with reference to preferred embodiments, this is not intended to limit the present invention. Persons skilled in the art will readily appreciate that various modifications and variations can be made without departing from the spirit and scope of the present 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: Bracket, end cover matched with the bracket, motor, controller, rotor and heat dissipation module arranged based on the bracket; The bracket is an annular structure, including a first mounting portion and a second mounting portion; the first mounting portion includes a mounting recess, an annular body, and a fixing plate; a transmission 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 transmission shaft; the second mounting portion includes a hollow body, which is coaxially arranged with the annular body; wherein the transmission shaft is a hollow shaft, and the fixing plate is used for detachably mounting the variable pitch motor; The end cover is movably mounted on the transmission shaft and includes a cover plate, a third mounting portion, and a fourth mounting portion. A plurality of mounting holes are formed on the outer periphery of the cover plate. The third mounting portion extends from the lower surface of the cover plate toward one side of the annular groove. The fourth mounting portion extends from the free end surface of the cover plate toward the annular body in a covering manner. The third mounting portion is provided with a first magnetic steel. 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 main body, and the rotor is fixed on the inner side wall of the fourth mounting portion and spaced apart from the stator; The controller includes a plurality of circuit boards, each of which is located in the second mounting portion; The heat dissipation module includes: a magnetic pump, a cooling chamber, a cooling coil, an oil cooler, a centrifugal fan and an air guide cover; the magnetic pump includes an oil pump and a second magnet, the oil pump is embedded in the annular groove, the second magnet is attached to the outer circumference of the oil pump, and is arranged opposite to the first magnet at intervals; the cooling chamber cover is arranged on the stator, including a fiber sleeve and a plurality of oil deflector rings; wherein the fiber sleeve is attached to the stator, and the oil deflector ring is fixed to the corresponding position of the end of the fiber sleeve and the annular main body; the oil cooler is placed in the second mounting part, including a plurality of cooling tubes and a plurality of heat dissipation fins, each cooling tube is arranged in an annular coil, and each heat dissipation fin is sequentially passed through the cooling tube; the cooling coil is fixedly mounted on the spare surface of each circuit board, and is placed on the inner side of the oil cooler together with each circuit board; the air guide cover is fixed to the bottom of the second mounting part; the centrifugal fan is axially passed through and fixed on the air guide cover; 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 fixing plate, and the rotating shaft is passed through the transmission shaft.

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

4. The aircraft electric drive assembly system according to claim 1, characterized in that: The transmission shaft and the bracket are separate structures, a circular hole is opened at the center of the mounting recess, and the transmission shaft is passed through and fixed in the circular hole; wherein, the transmission shaft is a steel shaft, and the bracket is a light alloy bracket.

5. The aircraft electric drive assembly system according to claim 1, characterized in that: The third mounting portion and the fourth mounting portion are separate structures. The third mounting portion is made of light metal, and the fourth mounting portion 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 portion is smaller than the radial dimension of the second mounting portion; the second mounting portion includes a connecting plate, and both ends of the connecting plate 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 a plurality of fixing interfaces; each fixing interface is spaced apart and opened at the lower end of the second mounting portion, and is used to fix the electric drive assembly system on the target aircraft.

8. The aircraft electric drive assembly system according to claim 1, characterized in that: The controller comprises a shell, which is located between the oil cooler and each circuit board and covers each circuit board.

9. The aircraft electric drive assembly system according to claim 1, characterized in that: A dust cover is included, and the dust cover is arranged 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 component, which is used to independently control the rotation speed of the centrifugal fan.

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