Electronically-controlled integrated water channel liquid cooling system for aerospace motor

Abstract

The invention relates to an aerospace motor electric control integrated water channel liquid cooling system which comprises a circular shell, an electric control cooling flow channel, a confluence channel and a motor internal flow channel. A cooling liquid flow channel is arranged in the circular shell, the electric control power module is fixedly installed in the shell, and a heat dissipation area of the electric control power module is directly attached to the inner wall of the electric control cooling flow channel. Cooling liquid enters the parallel shunting structure through the liquid inlet, the confluence channel is in seamless butt joint with an internal flow channel of the motor through a communication hole with a preset diameter, and a flow guide slope is machined at the inlet end of the communication hole to reduce fluid impact. The design of the quick-release flange connector and the sealing groove simplifies the assembly process, and the service life of the flow channel is prolonged through the anti-corrosion coating. The temperature sensor is arranged on the inner wall of the liquid outlet and monitors the temperature change of the cooling liquid in real time. According to the invention, the multi-interface defect of traditional hose connection is eliminated, the heat dissipation path and the space utilization rate are optimized, the leakage risk and the pressure loss are effectively reduced, and the requirements of aerospace equipment on light weight, high reliability and extreme environment adaptability are met.

Description

Technical Field

[0001] This invention relates to the field of motor and electronic control systems for aerospace equipment, and in particular to an integrated water-cooled system for aerospace motor and electronic control. Background Technology

[0002] In liquid cooling systems for aerospace motors and electronic control equipment, traditional cooling solutions typically rely on external hose connections for coolant circulation. In such designs, the coolant transfer from the controller to the motor requires multiple hose segments connected in series. Hose selection necessitates careful consideration of material temperature resistance, pressure resistance, interface sealing, and installation space constraints, leading to high system assembly complexity and increased maintenance costs. Hose connections introduce numerous joints and bends, increasing flow resistance and pressure loss, and increasing the risk of leakage due to vibration or aging. This significantly reduces reliability, especially under the high-frequency vibration and extreme temperature variations of aerospace equipment.

[0003] Furthermore, the dispersed nature of the hose layout leads to redundant coolant flow channels, making compact design difficult and limiting equipment lightweighting and space utilization. The conflict between the heat dissipation requirements of high-thermal-power modules and coolant distribution efficiency is further exacerbated, as traditional solutions struggle to achieve differentiated heat dissipation through dynamic flow adjustment. Therefore, a highly integrated liquid cooling system is urgently needed. This system should eliminate hose connection defects through integrated flow channel design and modular heat dissipation path optimization, while simultaneously improving heat dissipation efficiency and system reliability to meet the stringent requirements of the aerospace industry for efficient thermal management and structural compactness. Summary of the Invention

[0004] To address the above problems, this invention provides an integrated aerospace motor and electronic control system with a water-cooled cooling system, comprising: A circular housing, wherein the circular housing is provided with a coolant flow channel; Coolant flow channel, which includes an electronically controlled cooling flow channel, a manifold channel, and an internal flow channel of the motor; An electronically controlled power module is fixedly installed inside the circular housing, including at least one heat-generating power module, the heat dissipation area of ​​which is in contact with the electronically controlled cooling channel; A parallel flow distribution structure is provided in the electronically controlled cooling channel to evenly distribute the coolant to the heat dissipation area of ​​the heat-generating power module. A flow channel is provided inside the circular housing. One end of the flow channel is connected to the electronically controlled cooling channel, and the other end is connected to the internal flow channel of the motor through a connecting hole. The coolant input through the inlet flows sequentially through the parallel flow splitting structure, the heat dissipation area of ​​the heat-generating power module, and the confluence channel, then flows into the internal flow channel of the motor through the connecting hole and is discharged from the outlet.

[0005] Furthermore, the electronically controlled cooling channel includes an annular main channel and a parallel branch structure. The parallel branch structure consists of multiple parallel branches, which are distributed circumferentially along the circular shell, and each parallel branch extends to the heat dissipation area of ​​the corresponding heat-generating power module.

[0006] Furthermore, the cross-sectional area of ​​the parallel branch is positively correlated with the heating power of the corresponding heating power module.

[0007] Furthermore, the annular main channel of the electronically controlled cooling channel is distributed in a serpentine pattern along the circumference inside the circular shell, and the inner wall of the electronically controlled cooling channel is provided with guide protrusions.

[0008] Furthermore, the diameter of the connecting hole is 12.5 mm, and the annular inner wall of the connecting hole is provided with a guide slope to guide the coolant into the internal flow channel of the motor.

[0009] Furthermore, the heat dissipation area of ​​the heat-generating power module is provided with multiple heat dissipation fins, which are embedded in the coolant flow channels and are arranged in an alternating pattern along the coolant flow direction to increase the turbulence effect.

[0010] Furthermore, the circular shell is provided with an anti-corrosion coating on the inner wall of the coolant flow channel, and the coolant flow channel is formed by an integrated casting process.

[0011] Furthermore, the inlet and outlet adopt a quick-release flange structure, and the connection surface of the flange structure is provided with a sealing groove.

[0012] Furthermore, the electrically controlled cooling channel corresponding to the heat dissipation area of ​​the heat-generating power module is provided with a flow distribution structure.

[0013] Furthermore, a temperature sensor is also included at the outlet location. The temperature sensor is fixed to the inner wall of the outlet via a mounting groove, the opening direction of which is perpendicular to the flow direction of the coolant.

[0014] The beneficial effects of this invention are: The aerospace motor and electronic control integrated water-cooled system of this invention integrates the electronic control cooling channel, the manifold channel, and the internal motor flow channel into a single structure through an integrated circular shell and built-in flow channel design. This completely eliminates the multiple interfaces and bends required by traditional hose connections, significantly reducing leakage risk and flow channel pressure loss. The parallel flow distribution structure, combined with the branch design with differentiated cross-sectional area distribution, can dynamically allocate coolant flow according to the heating characteristics of the power module, achieving priority heat dissipation in high-heat areas. At the same time, the serpentine flow channel and guide protrusions enhance the coolant turbulence effect, improve heat exchange efficiency, and thus maintain the system temperature rise stability under complex operating conditions.

[0015] Furthermore, the quick-release flange interface and integrated casting process simplify the assembly process and reduce maintenance costs, while the anti-corrosion coating and flow guide slope design further extend the flow channel life and optimize fluid guidance performance. Through modular heat dissipation paths and a compact layout, the system improves space utilization while reducing connecting components, meeting the comprehensive requirements of aerospace equipment for lightweight, high reliability, and environmental adaptability, and providing an effective technical solution to the problems of structural redundancy and insufficient efficiency in traditional liquid cooling systems. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the internal structure of an integrated water-cooled system for aerospace motor and electronic control. Figure 2 This is a schematic diagram of the water flow direction in a parallel flow splitting structure of an integrated water cooling system for aerospace motors and electronic controls.

[0017] Among them, 1. circular shell; 2. parallel flow distribution structure; 3. connecting hole; 4. liquid inlet; 5. liquid outlet; 6. internal flow channel of motor. Detailed Implementation

[0018] The following is in conjunction with the appendix Figure 1-2 The preferred embodiments of the present invention will be described in detail so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more explicit definition of the scope of protection of the present invention.

[0019] The aerospace motor and electronic control integrated water-cooled system of this invention integrates the electronic control cooling channel, the confluence channel, and the motor internal channel 6 into a continuous closed structure through the integrated design of the circular shell 1 and the built-in flow channel. This directly eliminates the multiple interfaces and bends required by traditional hose connections. After the coolant enters the electronic control cooling channel through the inlet 4, it is evenly distributed to the heat dissipation area of ​​each heat-generating module through multiple branches of the parallel distribution structure 2. The cross-sectional area of ​​the branches is designed according to the different heat generation power of the modules, so that high-heat modules can obtain a larger flow rate and avoid local overheating. The serpentine distribution of the flow channel, combined with the inner wall guiding protrusions, forcibly changes the flow direction of the coolant, enhances the turbulence effect, thereby improving the heat exchange efficiency and solving the problems of flow channel redundancy and uneven heat dissipation in traditional hose systems.

[0020] Furthermore, the manifold seamlessly connects to the internal flow channel 6 of the motor via the connecting hole 3. The coolant flows smoothly into the motor after being guided by the guide slope, reducing fluid impact and pressure loss. The quick-release flange interface and integrated casting process simplify the housing assembly process and reduce the risk of leakage caused by the connection of multiple components. Meanwhile, the anti-corrosion coating and heat dissipation fin array extend the system life and adapt to high power density heat dissipation requirements from the dimensions of material durability and heat dissipation area expansion, respectively.

[0021] In addition, a temperature sensor is integrated into the inner wall of the outlet 5 to monitor coolant temperature changes in real time, providing data support for dynamic optimization of the heat dissipation path. Through modular layout and compact flow channel design, the system significantly improves space utilization and seismic performance while reducing external connection components, meeting the high reliability requirements of aerospace equipment under extreme vibration and temperature change environments, and systematically solving the defects of traditional solutions such as loose structure, complex maintenance and insufficient environmental adaptability.

[0022] The circular shell 1, serving as the fundamental load-bearing component of the entire liquid cooling system, is constructed from aerospace-grade aluminum or titanium alloy to ensure sufficient strength and lightweight operation in aerospace environments. Coolant channels are housed within the circular shell 1, and their layout can be circumferential, axial, or a combination thereof to accommodate different heat dissipation requirements. The coolant channels are formed using an integrated casting process, such as sand casting or low-pressure casting, ensuring the integrity and sealing of the channels. An anti-corrosion coating, such as an anodized layer or epoxy resin coating, is applied to the inner wall of the coolant channels to prevent corrosion of the shell by the coolant, extending the system's service life. With the circular shell 1 as the core carrier, it integrates the electronically controlled cooling channels, the manifold, and the internal motor channels 6, forming a continuous, closed coolant circulation path. The circular shell 1 is formed using an integrated casting process, and the inner wall of the channels is covered with an anti-corrosion coating to enhance corrosion resistance and durability. The electronically controlled power module is fixedly installed within the shell, with its heat dissipation area directly contacting the inner wall of the electronically controlled cooling channels, achieving efficient heat transfer through a metal thermal interface material. After the coolant enters the electronically controlled cooling channel through the inlet 4, it is evenly distributed to the heat dissipation area of ​​each heat-generating power module through multiple parallel branches of the parallel flow distribution structure 2. The branches are evenly distributed along the circumference of the shell, and the cross-sectional area is designed according to the heat generation power of the modules, so that the cross-sectional area of ​​the branch corresponding to the high-heat modules is larger, thus realizing adaptive flow distribution.

[0023] The electronically controlled cooling channel comprises an annular main channel and a parallel branching structure 2. The annular main channel can have a rectangular or circular cross-section; a rectangular cross-section facilitates processing and installation, while a circular cross-section reduces coolant flow resistance. The parallel branching structure 2 consists of multiple parallel branches distributed circumferentially along the circular housing 1. These branches can be evenly spaced or adjusted according to the position of the heat-generating modules. The cross-sectional area of ​​the parallel branches is positively correlated with the heat-generating power of the corresponding heat-generating modules. For modules with high heat-generating power, the corresponding branch cross-sectional area is larger to ensure sufficient coolant flow for heat dissipation. The electronically controlled cooling channel is serpentinely distributed circumferentially within the circular housing 1, with multiple arc-shaped connections. This distribution increases the coolant flow path and residence time, improving heat dissipation. Simultaneously, the inner wall of the electronically controlled cooling channel is provided with guide protrusions, which can be triangular or semi-circular in shape. These protrusions disrupt the laminar boundary layer of the coolant, enhancing turbulence and improving heat dissipation efficiency.

[0024] The electronically controlled power module is fixedly installed inside the circular housing 1. The heat dissipation area of ​​the heat-generating power module is in contact with the electronically controlled cooling channel. The contact method can be surface contact or embedded contact to ensure good heat conduction. The heat dissipation area is equipped with multiple heat dissipation fins, which are staggered along the coolant flow direction. Adjacent fins are offset at a certain angle. This arrangement can further enhance the turbulence effect and improve heat dissipation performance.

[0025] The parallel flow distribution structure 2 is located within the electronically controlled cooling channel to evenly distribute the coolant to the heat dissipation area of ​​the power module. A flow distribution structure, which can be a throttling orifice or an adjustable valve, is installed at the branch inlet to adjust the coolant flow rate according to actual heat dissipation requirements.

[0026] The manifold is located inside the circular housing 1, with one end connected to the electronically controlled cooling channel and the other end connected to the internal flow channel 6 of the motor via the connecting hole 3. The cross-section of the manifold can be designed to gradually expand or contract to accommodate the flow state of the coolant. The diameter of the connecting hole 3 is 12.5 mm, a size determined based on parameters such as the system's coolant flow rate and pressure. The annular inner wall of the connecting hole 3 is provided with a guide slope to guide the coolant smoothly into the internal flow channel 6 of the motor, reducing flow resistance.

[0027] The inlet 4 and outlet 5 adopt a quick-release flange structure, and the connection method is bolt connection, which facilitates the installation and maintenance of the system. The connection surface of the flange structure has a sealing groove, which can be rectangular or O-shaped. The sealing element can be a rubber sealing ring or a metal gasket to ensure the sealing of the connection and prevent coolant leakage.

[0028] The electrically controlled cooling channels are serpentinely distributed circumferentially within the housing. The inner walls of the channels are equipped with spiral guide protrusions to forcibly alter the coolant flow direction, enhancing turbulence and improving heat dissipation efficiency. The heat dissipation area of ​​the power module incorporates an array of staggered heat dissipation fins that extend into the channels, further increasing the heat exchange area and disturbing the flow field. The electrically controlled cooling channels are serpentinely distributed circumferentially within the housing, with spiral guide protrusions machined on the inner walls. The height of these protrusions is 1 / 5 to 1 / 4 of the channel height, used to enhance the coolant turbulence effect. The heat dissipation area of ​​the power module is connected to an array of heat dissipation fins. The fins are 1-2 mm thick and staggered along the coolant flow direction with a spacing of 3-5 mm to expand the heat exchange area and disturb the laminar boundary layer. The manifold is connected to the internal flow channel 6 of the motor via a 12.5mm diameter connecting hole 3. The inner wall of the inlet end of the connecting hole 3 is machined with a guide slope at an angle of 30°-45° to guide the coolant to flow smoothly into the motor flow channel and reduce pressure loss caused by fluid impact. A quick-release flange structure is located at the inlet 4 and the outlet 5. The connecting surface is machined with an annular sealing groove and an elastic sealing ring is installed. Quick assembly and reliable sealing are achieved by bolt tightening.

[0029] The temperature sensor is fixed to the inner wall of the outlet 5 via a mounting groove. The mounting groove can be fixed using an interference fit or a threaded connection. The opening direction of the mounting groove is perpendicular to the coolant flow direction, reducing interference with the coolant flow rate and ensuring the accuracy of temperature measurement. This also prevents the sensor probe from being directly impacted by the fluid, ensuring the stability of the measurement data. The flow distribution structure uses a throttling plate array, located within the electrically controlled cooling channel corresponding to the high-thermal-power module. Local flow is dynamically controlled by adjusting the spacing of the throttling plates. Through integrated housing design and modular layout, all structures work together to eliminate the multi-interface defects of traditional hose connections, while optimizing flow resistance and heat exchange performance, meeting the requirements of aerospace equipment for lightweight design, high reliability, and adaptability to complex operating conditions.

[0030] In the entire liquid cooling system, the coolant entering through inlet 4 first passes through the parallel distribution structure 2, where it is evenly distributed to the heat dissipation areas of each heat-generating power module, carrying away the heat generated by the power modules. Then, the coolant flows through the confluence channel and through the connecting hole 3 into the internal flow channel 6 of the motor, continuing to dissipate heat from the motor, and finally exits from outlet 5. A temperature sensor monitors the temperature of the coolant at outlet 5 in real time, providing feedback information for the system's heat dissipation control.

[0031] Any embodiment of the present invention can be used as an independent technical solution or in combination with other embodiments. All patents and publications mentioned in this specification represent publicly available technologies that can be used with the present invention. All patents and publications cited herein are also listed in the references as if each publication were individually referenced. The present invention can be implemented in the absence of any one or more elements, or one or more limitations, which are not specifically stated herein. The terminology and expressions used herein are descriptive methods and are not intended to be limiting, nor is there any intention to exclude any equivalent features from the terms and interpretations described herein; however, it is understood that any suitable changes or modifications can be made within the scope of the invention and the claims. It is understood that the embodiments described herein are embodiments and features in some examples, and any modifications and variations can be made by those skilled in the art based on the spirit of the description, and such modifications and variations are also considered to fall within the scope of the invention and the limitations of the independent and appended claims.

Claims

1. An integrated water-cooled system for aerospace motors and electronic controls, characterized in that, include: A circular housing, wherein the circular housing is provided with a coolant flow channel; Coolant flow channel, which includes an electronically controlled cooling flow channel, a manifold channel, and an internal flow channel of the motor; An electronically controlled power module is fixedly installed inside the circular housing, including at least one heat-generating power module, the heat dissipation area of ​​which is in contact with the electronically controlled cooling channel; A parallel flow distribution structure is provided in the electronically controlled cooling channel to evenly distribute the coolant to the heat dissipation area of ​​the heat-generating power module. A flow channel is provided inside the circular housing. One end of the flow channel is connected to the electronically controlled cooling channel, and the other end is connected to the internal flow channel of the motor through a connecting hole. The coolant input through the inlet flows sequentially through the parallel flow splitting structure, the heat dissipation area of ​​the heat-generating power module, and the confluence channel, then flows into the internal flow channel of the motor through the connecting hole and is discharged from the outlet.

2. The integrated water-cooled system for aerospace motors and electronic controls according to claim 1, characterized in that, The electronically controlled cooling channel includes an annular main channel and a parallel branch structure. The parallel branch structure consists of multiple parallel branches, which are distributed circumferentially along the circular shell, and each parallel branch extends to the heat dissipation area of ​​the corresponding heat-generating power module.

3. The integrated water-cooled system for aerospace motors and electronic controls according to claim 2, characterized in that, The cross-sectional area of ​​the parallel branch is positively correlated with the heating power of the corresponding heating power module.

4. The integrated water-cooled system for aerospace motors and electronic controls according to claim 2, characterized in that, The annular main channel of the electronically controlled cooling channel is distributed in a serpentine pattern along the circumference inside the circular shell, and the inner wall of the electronically controlled cooling channel is provided with guide protrusions.

5. The integrated water-cooled system for aerospace motors and electronic controls according to claim 1, characterized in that, The diameter of the connecting hole is 12.5 mm, and the annular inner wall of the connecting hole is provided with a guide slope to guide the coolant into the internal flow channel of the motor.

6. The aerospace motor and electronic control integrated water-cooled system according to claim 1, characterized in that, The heat dissipation area of ​​the heat-generating power module is provided with multiple heat dissipation fins, which are embedded in the coolant flow channel and are arranged alternately along the coolant flow direction to increase the turbulence effect.

7. The integrated water-cooled system for aerospace motors and electronic controls according to claim 1, characterized in that, The circular shell has an anti-corrosion coating on the inner wall of the coolant flow channel, which is formed by an integrated casting process.

8. The integrated water-cooled system for aerospace motors and electronic controls according to claim 1, characterized in that, The inlet and outlet are equipped with quick-release flanges, and the connection surfaces of the flanges are provided with sealing grooves.

9. The integrated water-cooled system for aerospace motors and electronic controls according to claim 1, characterized in that, The electronically controlled cooling channel corresponding to the heat dissipation area of ​​the heat-generating power module is equipped with a flow distribution structure.

10. The integrated water-cooled system for aerospace motors and electronic controls according to claim 1, characterized in that, The outlet also includes a temperature sensor, which is fixed to the inner wall of the outlet via a mounting groove, the opening of which is perpendicular to the flow direction of the coolant.

Images