An aircraft propulsion motor having a heating structure

Abstract

This invention discloses an aircraft propulsion motor with a heating structure, relating to the field of motor technology, to solve the problem of unstable motor operation under different operating conditions. It includes a housing, a power unit, a motor shaft, bearings, and a controller. A partition is provided inside the housing, dividing the internal space into a motor cavity and a controller cavity. The motor cavity houses the power unit, which drives the motor shaft to rotate. The controller cavity houses the controller, which controls the operation or shutdown of the power unit. A bearing chamber is provided within the motor cavity, and bearings are installed within the bearing chamber. The motor shaft is rotatably connected to the housing via the bearings. The aircraft propulsion motor with a heating structure provided by this invention is used in aircraft propulsion motors.

Description

Technical Field

[0001] This invention relates to the field of motor technology, and more particularly to an aircraft propulsion motor with a heating structure. Background Technology

[0002] The propulsion motor operates in a high-altitude, low-temperature, and low-pressure environment. During operation, the rotor and other components generate heat, causing the motor to heat up. When the propulsion motor stops working, it is rapidly cooled by the external air. Throughout the entire operation of the propulsion motor, its temperature ranges from approximately -85℃ to +50℃, and its pressure ranges from approximately 5 kPa to 101 kPa. This significant variation in operating conditions can lead to problems such as freezing and accelerated evaporation of bearing grease, as well as deformation of the mechanism.

[0003] To adapt to different working conditions, a temperature-controlled heating plate is usually installed close to the motor driver. Because the temperature-controlled heating plate is close to the driver, the motor is heated unevenly, which leads to unstable motor operation. Summary of the Invention

[0004] The purpose of this invention is to provide an aircraft propulsion motor with a heating structure to solve the problem of unstable operation of the motor under different operating conditions.

[0005] This invention provides an aircraft propulsion motor with a heating structure, including a housing, a power unit, a motor shaft, a bearing, and a controller. A partition is provided inside the housing, dividing the internal space into a motor cavity and a controller cavity. The motor cavity houses the power unit, which drives the motor shaft to rotate. The controller cavity houses the controller, which controls the operation or shutdown of the power unit. A bearing chamber is provided within the motor cavity, and the bearing is installed inside the bearing chamber. The motor shaft is rotatably connected to the housing via the bearing. A first heating structure and a first temperature sensor mounted on the first heating structure are provided on the side of the partition near the controller. Both the first heating structure and the first temperature sensor are electrically connected to the controller. If the first temperature sensor detects that the temperature of the controller cavity is less than or equal to a preset temperature, the controller controls the first heating structure to heat up.

[0006] Compared with existing technologies, the aircraft propulsion motor with a heating structure provided by this invention has a partition inside the housing, which divides the internal space of the housing into a motor cavity and a controller cavity. The motor cavity is used to house the power unit, which drives the motor shaft to rotate. Since a bearing chamber is located within the motor cavity, and the bearing is installed in the bearing chamber, the motor shaft is rotatably connected to the housing through the bearing. Therefore, when the motor shaft rotates, the friction between the motor shaft and the bearing generates a large amount of heat, as do the heat generated by the power unit and the controller. When the motor shaft stops rotating, the bearing gradually cools down. The heat generated or the cooling of the bearing affects the bearing grease inside, causing it to evaporate faster or freeze. Accelerated evaporation or freezing of the bearing grease can lead to unstable bearing operation, resulting in overall motor instability. Therefore, the first heating structure is located on the side of the partition closer to the controller, and the first temperature sensor... A temperature sensor installed on the first heating structure can detect temperature changes in the controller cavity when the motor shaft rotates or stops. When the temperature inside the controller cavity is detected to be less than or equal to a preset temperature, the controller controls the first heating structure to start heating, ensuring that the controller maintains a constant temperature whether it is working or not. This provides a stable working environment for the components inside the controller and effectively solves the problem of component failure due to unstable operating conditions. At the same time, the temperature inside the bearing chamber is maintained within a preset temperature range, preventing the bearing grease from evaporating or freezing under different motor operating conditions, and effectively solving the problem of unstable motor operation under different operating conditions. Attached Figure Description

[0007] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0008] Figure 1 A perspective view of an aircraft propulsion motor with a heating structure, according to an exemplary embodiment of the present invention, is shown.

[0009] Figure 2 A cross-sectional view of an aircraft propulsion motor with a heating structure, according to an exemplary embodiment of the present invention, is shown.

[0010] Figure 3 An exemplary embodiment of the present invention is shown. Figure 2 A magnified view of point B in the image;

[0011] Figure 4 An exemplary embodiment of the present invention is shown. Figure 2 A magnified view of point A in the image.

[0012] Figure 5A cross-sectional view of a controller according to an exemplary embodiment of the present invention is shown.

[0013] Figure label:

[0014] 1-Housing, 101-Motor housing, 102-Controller housing, 2-Power unit, 3-Motor shaft, 4-Bearing, 5-Controller, 6-Partition plate, 7-First heating structure, 8-First temperature sensor, 9-Second heating structure, 10-Second temperature sensor, 11-First heat dissipation structure, 21-Limiting cover. Detailed Implementation

[0015] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0016] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0017] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0018] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0019] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0020] The propulsion motor operates in a high-altitude, low-temperature, and low-pressure environment. During operation, the rotor and other components generate heat, causing the motor to heat up. When the propulsion motor stops working, it is rapidly cooled by the external air. Throughout the entire operation of the propulsion motor, its temperature ranges from approximately -85℃ to +50℃, and its pressure ranges from approximately 5 kPa to 101 kPa. This significant variation in operating conditions can lead to problems such as freezing and accelerated evaporation of bearing grease, as well as deformation of the mechanism.

[0021] To adapt to different working conditions, a temperature-controlled heating plate is usually installed close to the motor driver. Because the temperature-controlled heating plate is close to the driver, the motor is heated unevenly, which leads to unstable motor operation.

[0022] To address the aforementioned problems, an exemplary embodiment of the present invention provides an aircraft propulsion motor with a heating structure to solve the problem of unstable motor operation under different operating conditions.

[0023] Figure 1 A perspective view of an aircraft propulsion motor with a heating structure, according to an exemplary embodiment of the present invention, is shown. Figure 2 A cross-sectional view of an aircraft propulsion motor with a heating structure, according to an exemplary embodiment of the present invention, is shown. Figures 1 to 2 As shown, the aircraft propulsion motor with a heating structure provided in the exemplary embodiment of the present invention includes: a housing 1, a power unit 2, a motor shaft 3, a bearing 4, and a controller 5; a partition 6 is provided inside the housing 1, dividing the internal space of the housing 1 into a motor cavity and a controller cavity, the motor cavity being used to accommodate the power unit 2, the power unit 2 being used to drive the motor shaft 3 to rotate, and the controller cavity being used to accommodate the controller 5, the controller 5 being used to control the operation or stop of the power unit 2; a bearing chamber is provided inside the motor cavity, the bearing 4 is installed inside the bearing chamber, and the motor shaft 3 is rotatably connected to the housing 1 through the bearing 4; a first heating structure 7 and a first temperature sensor 8 installed on the first heating structure 7 are provided on the side of the partition 6 near the controller 5, both the first heating structure 7 and the first temperature sensor 8 are electrically connected to the controller 5, if the first temperature sensor 8 detects that the temperature of the controller cavity 102 is less than or equal to a preset temperature, the controller 5 controls the first heating structure 7 to heat up.

[0024] In specific implementation, such as Figures 1 to 2 As shown in the exemplary embodiment of the present invention, in the aircraft propulsion motor with a heating structure, a partition 6 is provided inside the housing 1. The partition 6 divides the internal space of the housing 1 into a motor cavity and a controller cavity. The motor cavity is used to accommodate the power unit 2, which is used to drive the motor shaft 3 to rotate. Since a bearing chamber is provided inside the motor cavity, and the bearing 4 is installed in the bearing chamber, the motor shaft 3 is rotatably connected to the housing 1 through the bearing 4. Therefore, when the motor shaft 3 rotates, the rotation of the motor shaft 3 and the friction with the bearing 4 generate a large amount of heat, as do the heat generated by the rotation of the power unit 2 and the heat generated by the controller 5. When the motor shaft 3 stops rotating, the motor shaft 3 and the bearing 4 stop rotating, and the bearing 4 gradually cools down. When the bearing 4 generates heat or cools down, the bearing grease inside the bearing 4 is affected, causing the bearing grease to evaporate faster or freeze. When the bearing grease evaporates faster or freezes, the bearing 4 will run unstablely, resulting in the overall unstable operation of the motor. At the same time, the controller 5 is the core component of the entire motor control, and its heating and heat preservation are crucial to the operation of the entire motor.

[0025] As can be seen from the above implementation process, Figure 3 An exemplary embodiment of the present invention is shown. Figure 2 A magnified view of point B in the image, as shown below. Figure 3 As shown, the first heating structure 7 is located on the side of the partition 6 near the controller, and the first temperature sensor 8 is located on the first heating structure 7. When the motor shaft rotates or stops rotating, the temperature sensor on the first heating structure 7 can be used to detect the temperature change of the controller cavity. When the temperature inside the controller cavity is detected to be less than or equal to the preset temperature, the controller controls the first heating structure 7 to start heating, so that the temperature of the controller is kept in a constant temperature state when it is working or not working, providing a stable working environment for the components inside the controller. This effectively solves the problem of component failure due to unstable operating conditions. At the same time, the temperature inside the bearing chamber is kept within the preset temperature range, which avoids the bearing grease from evaporating too quickly or freezing under different motor operating conditions, effectively solving the problem of unstable motor operation under different operating conditions.

[0026] For example, the first heating structure is an electrothermal film, which is wrapped around the part of the partition near the controller. The electrothermal film is an electrothermal material, and its principle is to use the heat generated when the current passes through the resistive material to heat the object. Specifically, in this invention, the controller controls the power module to supply power to the electrothermal film, and the current passes through the electrothermal film to generate heat, thereby increasing the temperature of the controller cavity. Since the electrothermal film has the advantages of high electrothermal conversion efficiency and good thermal conductivity, the first heating structure located on the part of the partition 6 near the controller can also achieve a heat preservation effect on the temperature of the bearing chamber.

[0027] For example, the bearing housing includes a front bearing housing, in which a front bearing is disposed. The front bearing housing is located near the drive end of the motor shaft. A second heating structure and a second temperature sensor mounted on the outer side wall of the front bearing housing are circumferentially disposed. Both the second heating structure and the second temperature sensor are electrically connected to the controller. When the bearing generates heat or cools down, the bearing grease inside the bearing is affected, causing the bearing grease to evaporate faster or freeze. When the bearing grease evaporates faster or freezes, the bearing operation becomes unstable, which in turn causes the overall motor operation to become unstable. At this time, if the second temperature sensor detects that the temperature inside the front bearing housing is less than or equal to a preset temperature, the controller controls the second heating structure to heat up.

[0028] For example, Figure 4 An exemplary embodiment of the present invention is shown. Figure 2 A magnified view of point A in the image, as shown below. Figure 4 As shown, the motor also includes a limiting cover 21, which is fastened to the outer periphery of the second heating structure 9 to fix the second heating structure 9.

[0029] In practical applications, since the second heating structure 9 is circumferentially arranged on the outer wall of the front bearing chamber, there is a gap between the periphery of the limiting cover 21 and the outer wall of the bearing chamber. Part of the second heating structure 9 is located in the gap. The limiting cover 21 presses and fixes the second heating structure 9 to the outer wall of the bearing chamber, preventing the second heating structure 9 from falling off due to bearing vibration. It can be understood that the limiting cover 21 can be a regular-shaped cover or an irregular-shaped cover. Taking an annular cover as an example, the motor shaft passes through the annular cover. When the motor shaft rotates, it rotates relative to the bearing. When the bearing rotates, it will cause shaking in the bearing chamber. The limiting cover 21 can increase the force of the second heating structure 9 towards the bearing chamber, preventing the second heating structure 9 from falling off when the bearing chamber shakes.

[0030] It should be understood that the second heating structure is an electrothermal film, which is wrapped around the outer wall of the bearing chamber near the internal space of the motor housing. Since the electrothermal film has the advantages of high electrothermal conversion efficiency and good thermal conductivity, the first heating structure located on the outer wall of the bearing chamber can achieve a heat preservation effect on the temperature inside the bearing chamber.

[0031] For example, the motor shaft passes through the motor cavity and the non-driving end extends through the partition into the controller cavity. The front bearing chamber is a cylindrical structure whose housing extends axially into the motor cavity along the motor shaft. The outer periphery of the cylindrical structure is provided with a second heating structure and a limiting cover for fixing the second heating structure. By setting the aforementioned front bearing chamber as a cylindrical structure, the entire motor body becomes more compact.

[0032] For example, the bearing housing also includes a rear bearing housing, which is located near the non-driving end of the motor shaft. The rear bearing housing is a cylindrical structure with a partition extending axially into the motor cavity along the motor shaft. The bearings are respectively placed in the front bearing housing and the rear bearing housing. The front bearing housing and the rear bearing housing can not only provide support for the motor shaft, but also provide insulation for the heat generated during the rotation of the bearing and the motor shaft.

[0033] In one alternative embodiment, a third heating structure and a third temperature sensor are provided on the outer periphery of the rear bearing chamber. Both the third heating structure and the third temperature sensor are electrically connected to the controller. If the third temperature sensor detects that the temperature inside the rear bearing chamber is less than or equal to a preset temperature, the controller controls the third heating structure to heat up. The third heating structure is an electrothermal film.

[0034] In practical applications, the third heating structure is located on the side of the motor housing near the controller, and the third temperature sensor is located on the third heating structure. During the rotation of the motor and the rotation of the motor shaft, the controller is used to perform operations such as starting, stopping, accelerating, decelerating, maintaining speed, and reversing the motor. Through the controller, we can accurately control the speed, torque, and position of the motor to ensure stable operation of the motor and achieve precise control of related systems. The controller is used to control the heating of the third heating structure, which can keep the rear bearing chamber warm, so that the temperature inside the rear bearing chamber is kept within the preset temperature range. Under different motor operating conditions, it avoids the accelerated evaporation or freezing of bearing grease, effectively solving the problem of unstable motor operation under different operating conditions.

[0035] The third heating structure is an electric heating film, which is wrapped around the outer wall of the bearing chamber near the internal space of the motor housing. Because the electric heating film has the advantages of high electrothermal conversion efficiency and good thermal conductivity, the first heating structure located on the outer wall of the bearing chamber can achieve a heat preservation effect on the temperature inside the bearing chamber.

[0036] For example, Figure 5 A cross-sectional view of a controller according to an exemplary embodiment of the present invention is shown, such as... Figure 5As shown, the first heating structure 7 is arranged circumferentially on the partition along the non-drive end of the motor shaft. The controller includes control components, power components, power supply components, and sensing components, etc. The control components, power components, power supply components, and sensing components are electrically connected to the controller, and each electrical component is integrated on the PCB board. The two sides of the PCB board are supported by the controller housing. The PCB board and the partition are arranged parallel to each other, and there is a certain distance between the partition and the controller. In order to avoid the space-consuming parts such as capacitors of the controller, the first heating structure is arc-shaped and can be arranged circumferentially around the non-drive end. The arc is about 240°. In order to meet the requirements of the motor in extreme temperature environment, the temperature of the front and rear bearings of the motor and the controller is controlled. In addition to heating the controller through thermal radiation, the heat generated by the first heating structure is transferred to the rear bearing chamber through thermal conduction, realizing the simultaneous heating of the controller and the rear bearing chamber by a single electrothermal film.

[0037] For example, a first temperature sensor is disposed on a first heating structure, a second temperature sensor is disposed on a second heating structure, and a third temperature sensor is disposed on a third heating structure. When the first temperature sensor detects that the temperature of the bearing chamber is less than or equal to a preset temperature, it can be understood that... Figure 5 The temperature sensor outputs a resistance signal to the amplifier component, where a voltage gain value is obtained. The first temperature sensor then sends a warning signal to the controller. This can also be understood as the voltage gain value exceeding the preset boost value. At this time, the temperature sensor inputs a warning signal to the controller, and the controller then controls the first heating structure to start heating. Similarly, the second and third temperature sensors operate in the same way as the first temperature sensor, which will not be elaborated here.

[0038] In one alternative approach, such as Figure 1 As shown, the housing includes a motor housing 101 and a controller housing 102. The controller is located inside the controller housing 102. The controller housing 102 is located at the non-driving end of the motor shaft. The end face of the controller housing near the motor housing has an opening. The motor shaft passes through the motor housing 101 and the non-driving end extends into the controller housing 102 through the opening.

[0039] In practical applications, the housing includes a motor housing and a controller housing. When the controller housing and motor housing are integrated into a single structure, not only is the structure compact, but the overall weight of the motor is also reduced. Furthermore, the controller housing is located at the non-drive end of the motor shaft, and its end face near the motor housing has an opening. When the motor is not in operation, the controller can transfer some heat to the motor housing through the controller housing during heat dissipation, thus providing insulation for the motor housing. Simultaneously, when the motor is in operation, the heat generated by the motor is transferred to the controller housing through the motor housing, thereby achieving heat dissipation for the motor.

[0040] In one alternative approach, such as Figure 1 As shown, the aircraft propulsion motor with a heating structure also includes a first heat dissipation structure 11, which is located on the outer wall of the shell.

[0041] In practical applications, the first heat dissipation structure can be a heat sink or other heat dissipation components. Here, we take a heat sink as an example. Part of the heat sink is inserted into the motor housing. When the motor generates electricity, some of the heat inside the motor can be transferred to the heat sink. The heat sink conducts the heat to the outside of the motor housing, thereby achieving cooling of the inside of the motor housing.

[0042] For example, the motor housing has a through hole and a breathable membrane formed in the through hole. The breathable membrane in the through hole can be used to balance the pressure difference between the inside and outside of the motor housing, so that the pressure inside and outside the motor housing remains balanced.

[0043] An exemplary embodiment of the present invention also provides an aircraft including a motor with a heating structure as described in the exemplary embodiment of the present invention. It should be understood that the aircraft in the embodiments of the present invention can be a drone or a manned aircraft. For example:

[0044] It should be noted that the aircraft provided in the embodiments of the present invention may also include a fuselage, a flight controller, etc., with the engine, flight controller, etc. located in the fuselage.

[0045] Compared with the prior art, the beneficial effects of the aircraft provided by the embodiments of the present invention are the same as the beneficial effects of the motor with heating structure provided by the embodiments of the present invention, and will not be repeated here.

[0046] Although the invention has been described in conjunction with specific features and embodiments, it is obvious that various modifications and combinations can be made therein without departing from the spirit and scope of the invention. Accordingly, this specification and drawings are merely exemplary descriptions of the invention as defined by the appended claims, and are considered to cover any and all modifications, variations, combinations, or equivalents within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if such modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include such modifications and modifications.

[0047] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. An aircraft propulsion motor having a heating structure, characterized in that, include: Housing, power unit, motor shaft, bearings, and controller; The housing is provided with a partition, which divides the internal space of the housing into a motor cavity and a controller cavity. The motor cavity is used to house the power device, which is used to drive the motor shaft to rotate. The controller cavity is used to house the controller, which is used to control the operation or stop of the power device. The motor cavity is provided with a bearing chamber, the bearing is installed in the bearing chamber, and the motor shaft is rotatably connected to the housing through the bearing; The partition is provided with a first heating structure and a first temperature sensor mounted on the first heating structure on the side closest to the controller. Both the first heating structure and the first temperature sensor are electrically connected to the controller. If the first temperature sensor detects that the temperature of the controller cavity is less than or equal to a preset temperature, the controller controls the first heating structure to heat up. The bearing housing also includes a rear bearing housing, which is located near the non-driving end of the motor shaft. The rear bearing housing is a cylindrical structure in which the partition extends axially into the motor cavity along the motor shaft. The controller includes a PCB board on which electronic components are integrated. The two sides of the PCB board are supported by the controller housing. The PCB board and the partition are arranged parallel to each other and spaced apart. The bearing chamber includes a front bearing chamber, and a second heating structure is circumferentially provided on the outer side wall of the front bearing chamber; the motor shaft passes through the motor cavity and the non-driving end extends through the partition into the controller cavity.

2. The aircraft propulsion motor with a heating structure of claim 1, wherein, The first heating structure is an electrothermal film.

3. The aircraft propulsion motor with a heating structure according to claim 1, characterized in that, The front bearing housing is provided with a front bearing, which is located near the drive end of the motor shaft. A second temperature sensor is circumferentially mounted on the second heating structure on the outer side wall of the front bearing housing. Both the second heating structure and the second temperature sensor are electrically connected to the controller. If the second temperature sensor detects that the temperature inside the front bearing housing is less than or equal to a preset temperature, the controller controls the second heating structure to heat up.

4. The aircraft propulsion motor with a heating structure according to claim 3, characterized in that, The motor with the heating structure also includes a limiting cover, which is fastened to the outer periphery of the second heating structure to fix the second heating structure.

5. The aircraft propulsion motor with a heating structure according to claim 4, characterized in that, The front bearing chamber is a cylindrical structure that extends from the housing into the motor cavity along the motor shaft. The outer periphery of the cylindrical structure is provided with a second heating structure and a limiting cover for fixing the second heating structure.

6. The aircraft propulsion motor with a heating structure according to claim 5, characterized in that, A third heating structure and a third temperature sensor installed on the outer periphery of the rear bearing chamber are provided. Both the third heating structure and the third temperature sensor are electrically connected to the controller. If the third temperature sensor detects that the temperature inside the rear bearing chamber is less than or equal to a preset temperature, the controller controls the third heating structure to heat up. The third heating structure is an electrothermal film.

7. The aircraft propulsion motor with a heating structure according to claim 5, characterized in that, The first heating structure is arranged circumferentially along the non-driving end of the motor shaft on the partition.

8. The aircraft propulsion motor with a heating structure according to claim 3, characterized in that, The second heating structure is an electrothermal film.

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