Thermal management device and aircraft

Abstract

The application relates to a heat management device and an aircraft, the heat management device comprising a power motor, a propeller, a wind tube and a supporting heat dissipation structure, the power motor driving the propeller to rotate; the wind tube is provided with a through duct, the wind tube is sleeved on the outer circumferential side of the power motor and the propeller through the duct; the power motor is installed on the duct through the supporting heat dissipation structure; the supporting heat dissipation structure is provided with a heat dissipation cavity, one end of the heat dissipation cavity is in heat conduction contact with the power motor, the other end extends towards the direction close to the wind tube, the heat dissipation cavity contains liquid working medium, the liquid working medium can be gasified by absorbing heat and flow along the extension direction of the heat dissipation cavity, and the propeller can form an airflow flowing along the axial direction of the wind tube in the duct, so that the gaseous working medium in the heat dissipation cavity can be liquefied by releasing heat and flow back to the end close to the power motor. The heat management device and the aircraft provided by the application solve the problem that the existing liquid cooling device is difficult to meet the heat dissipation requirement of the power motor.

Description

Technical Field

[0001] This application relates to the field of flight device technology, and in particular to a thermal management device and an aircraft. Background Technology

[0002] In the field of electric aircraft (such as electric vertical takeoff and landing aircraft), the heat generated by the motor is often very large. Therefore, heat dissipation of the motor (especially the stator windings) has become a key concern. Current technologies primarily rely on heat transfer through contact between the motor housing and liquid cooling plates or oil immersion for cooling. However, with the significant increase in motor power, current liquid cooling systems are no longer sufficient to meet the heat dissipation requirements. If the heat from the motor cannot be dissipated in time, it may lead to motor damage and even directly affect the flight safety of the aircraft. Summary of the Invention

[0003] Therefore, it is necessary to provide a thermal management device and an aircraft to solve the problem that existing liquid cooling devices cannot meet the heat dissipation requirements of power motors.

[0004] The thermal management device provided in this application includes a power motor, a propeller, a fan duct, and a supporting heat dissipation structure. The propeller is connected to the output end of the power motor, which can drive the propeller to rotate. The fan duct has a duct that runs through it along its own axis. The fan duct is fitted onto the outer periphery of the power motor and the propeller through the duct. The power motor is installed in the duct through the supporting heat dissipation structure. The supporting heat dissipation structure has a heat dissipation cavity. One end of the heat dissipation cavity is in thermal contact with the power motor, and the other end extends towards the direction close to the fan duct. The heat dissipation cavity contains a liquid working fluid. The liquid working fluid can absorb heat and vaporize, and flow along the extension direction of the heat dissipation cavity. The propeller can form an airflow in the duct that flows along the axial direction of the fan duct, so that the gaseous working fluid in the heat dissipation cavity can release heat, liquefy, and flow back to the end close to the power motor.

[0005] In one embodiment, the supporting heat dissipation structure includes an evaporation section and a supporting tube. The evaporation section and the heating end of the power motor are in thermal contact. One end of the supporting tube is fixedly connected to the outer periphery of the evaporation section, and the other end is supported and connected to the inner wall of the air duct. Multiple supporting tubes are distributed at intervals along the outer periphery of the evaporation section. The heat dissipation cavity includes an evaporation cavity and a condensation cavity. The evaporation cavity is located in the evaporation section and contains a liquid working fluid. At least a portion of the supporting tubes are provided with condensation cavities. One end of each condensation cavity is connected to the evaporation cavity, and the other end extends toward the direction close to the inner wall of the air duct.

[0006] In one embodiment, the height of the end of the condenser tube furthest from the evaporator is greater than the maximum height of the evaporator.

[0007] In one embodiment, a supporting tube with a condenser cavity is defined as a condenser tube, which extends radially toward the upper end of the air duct; multiple condenser tubes are arranged circumferentially along the evaporation section to form a fan-shaped heat dissipation area, and the central angle A corresponding to the heat dissipation area satisfies 15°≤A<180°.

[0008] In one embodiment, the liquid working fluid located in the evaporation chamber and the heating surface of the power motor are in contact through the side wall of the evaporation section; the evaporation section is attached to one side of the stator winding of the power motor, or the stator winding of the power motor is at least partially immersed in the liquid working fluid of the evaporation chamber.

[0009] In one embodiment, the air duct is provided with a balancing cavity that extends circumferentially along the air duct, and the ends of multiple condensing tube cavities away from the evaporation cavity are respectively connected to the balancing cavity; the supporting heat dissipation structure also includes a branch tube body, one end of which is connected to the condensing tube body, and the other end of which is connected to the inner wall of the air duct or an adjacent condensing tube body. The heat dissipation cavity also includes a branch tube cavity, which is located in the branch tube body. One end of the branch tube cavity is connected to the condensing tube cavity, and the other end of which is connected to the balancing cavity or an adjacent condensing tube cavity.

[0010] In one embodiment, when the extension direction of the support tube is not vertical, the upper end of the support tube is provided with an arc-shaped lifting surface, and the height of the lifting surface first increases and then decreases along the direction from the front side to the rear side of the aircraft; when the extension direction of the support tube is vertical, the two ends of the support tube are symmetrically arranged, and the cross-section of the support tube is teardrop-shaped.

[0011] In one embodiment, the evaporation chamber includes a reflux channel and a collection chamber. Multiple condenser tubes are distributed and connected to the outer periphery of the reflux channel. The collection chamber is located at one end of the reflux channel near the power motor and is connected to the reflux channel. The collection chamber and the heating end of the power motor are in thermal contact. The end of the reflux channel connected to the collection chamber is provided with an expansion cavity. Along the direction from the reflux channel to the collection chamber, the flow area of ​​the expansion cavity tends to increase.

[0012] In one embodiment, the supporting heat dissipation structure further includes a pumping assembly, a delivery pipe, and a baffle plate. The lower end of the baffle plate is sealed to the inner wall of the collecting cavity and divides the collecting cavity into a first cavity near the return channel and a second cavity near the power motor. The upper end of the baffle plate and the inner wall of the collecting cavity are spaced apart to form a vapor channel. The liquid working fluid returning from the condenser cavity can enter the first cavity through the lower region of the return channel. One end of the delivery pipe is immersed in the liquid working fluid in the first cavity, and the other end crosses the vapor channel and extends into the second cavity. The pumping assembly can deliver the liquid working fluid from the first cavity to the second cavity through the delivery pipe. The liquid working fluid in the second cavity can absorb heat and vaporize into a gaseous working fluid and enter the condenser cavity through the vapor channel and the upper region of the return channel.

[0013] In one embodiment, the flow area of ​​the vapor passage is greater than or equal to the flow area of ​​the reflux passage, and the flow area of ​​the reflux passage is greater than or equal to the sum of the flow areas of the plurality of condenser cavities.

[0014] In one embodiment, the pumping component is a magnetic coupling pump, which includes a magnetic actuator and a magnetic impeller assembly. The magnetic actuator is directly mounted on the output end of the power motor or mounted on the output end of the power motor through a transmission assembly. The power motor can drive the magnetic actuator to rotate. The magnetic impeller assembly is installed inside the delivery pipe. When the power motor is working, the rotating magnetic field of the magnetic actuator can drive the magnetic impeller assembly to rotate synchronously. The centrifugal force generated by the magnetic impeller assembly can pump the liquid working fluid in the first chamber into the delivery pipe and deliver it to the second chamber.

[0015] In one embodiment, the pumping assembly includes a controller, a liquid pump, and a liquid level sensor, wherein the liquid level sensor is disposed in a first chamber or a second chamber. When the liquid level sensor is disposed in the first chamber and measures that the liquid level of the working medium in the first chamber is higher than a first preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first chamber to the second chamber through a delivery pipe. Alternatively, when the liquid level sensor is disposed in the second chamber and measures that the liquid level of the working medium in the second chamber is lower than a second preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first chamber to the second chamber through a delivery pipe.

[0016] In one embodiment, the heat dissipation support structure is located on the front side of the aircraft, and the propeller is located on the rear side of the aircraft.

[0017] This application also provides an aircraft that includes the thermal management device described in any of the above embodiments.

[0018] Compared with existing technologies, the thermal management device and aircraft provided in this application transfer the heat generated by the power motor to the liquid working fluid in the heat dissipation chamber, utilizing the phase change of the working fluid to achieve efficient heat absorption. Simultaneously, the forced airflow generated by the propeller cools the heat dissipation chamber, causing the gaseous working fluid to release heat, liquefy, and flow back, forming an efficient thermal cycle. Therefore, this device effectively solves the problem that existing liquid cooling devices cannot meet the heat dissipation requirements of high-power power motors, ensuring the stability and reliability of the power motor under long-term high-load operation, thereby improving the flight safety of electric aircraft. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the conventional technology, the drawings used in the description of the embodiments or the conventional technology will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A schematic diagram of the structure of a thermal management device according to an embodiment of this application;

[0021] Figure 2 A partial three-dimensional view of a thermal management device according to an embodiment of this application;

[0022] Figure 3 for Figure 2 A sectional view of the structure shown and a cross-sectional view of the supporting tube at the corresponding location;

[0023] Figure 4 A cross-sectional view of a thermal management device according to another embodiment of this application;

[0024] Figure 5 A cross-sectional view of a thermal management device according to another embodiment provided in this application;

[0025] Figure 6 A partial cross-sectional view of a thermal management device according to an embodiment of this application.

[0026] Reference numerals: 100, Power motor; 200, Propeller; 300, Fan; 310, Duct; 320, Balance chamber; 400, Supporting heat dissipation structure; 410, Heat dissipation chamber; 420, Evaporator; 421, Evaporation chamber; 422, Return channel; 423, Collection chamber; 424, First chamber; 425, Second chamber; 426, Expanding cavity; 430, Supporting pipe; 431, Condensation chamber; 432, Lifting surface; 440, Branch pipe; 441, Branch chamber; 450, Fin; 460, Pumping assembly; 470, Delivery pipe; 480, Baffle plate; 490, Steam channel; 500, Head guide shroud; 600, Tail guide shroud. Detailed Implementation

[0027] Current liquid cooling devices are no longer sufficient to meet the cooling requirements of electric aircraft motors due to the significant increase in motor power. If the heat from the motor cannot be dissipated in time, it may lead to limited output power or even damage to the motor, directly affecting the flight safety of the aircraft.

[0028] Please see Figures 1-6In one embodiment, this application proposes a thermal management device, including a power motor 100, a propeller 200, a fan duct 300, and a supporting heat dissipation structure 400. The propeller 200 is connected to the output end of the power motor 100, which drives the propeller 200 to rotate. The fan duct 300 has a duct 310 extending along its axial direction. The fan duct 300 is fitted onto the outer periphery of the power motor 100 and the propeller 200 through the duct 310. One end of the supporting heat dissipation structure 400 is connected to the power motor 100, and the other end is connected to the inner wall of the duct 310, so that the power motor 100 can be mounted on the duct 310 through the supporting heat dissipation structure 400. The supporting heat dissipation structure 400 is provided with a heat dissipation cavity 410. One end of the heat dissipation cavity 410 is in thermal contact with the power motor 100, and the other end extends toward the direction close to the air duct 300. The heat dissipation cavity 410 contains a liquid working medium. The liquid working medium can absorb heat and vaporize and flow along the extension direction of the heat dissipation cavity 410. The propeller 200 can form an airflow along the axial direction of the air duct 300 in the duct 310, so that the gaseous working medium in the heat dissipation cavity 410 can release heat, liquefy and flow back to the end close to the power motor 100.

[0029] The thermal management device provided in this embodiment is based on the principle of achieving efficient heat dissipation of the power motor 100 by combining phase change heat transfer with forced convection.

[0030] Specifically, the power motor 100, as the core component for energy conversion, has its output end connected to the propeller 200. The power motor 100 drives the propeller 200 to rotate using electrical energy, thereby providing thrust to the aircraft. For example, the shaft of the power motor 100 is directly connected to the hub of the propeller 200, or indirectly connected through a reduction gear set, to match the optimal speed of the propeller 200. Furthermore, the air duct 300 serves to guide airflow and provide some protection to internal components. For example, the air duct 300 can be a cylindrical structure with a smooth inner wall to reduce airflow resistance and ensure efficient airflow through the duct 310. Further, the supporting heat dissipation structure 400 can be composed of multiple solid or hollow metal brackets, which are fixed between the housing of the power motor 100 and the inner wall of the duct 310 by bolts or welding, thereby providing mechanical support.

[0031] The heat dissipation structure 400 has a heat dissipation cavity 410 inside. One end of the heat dissipation cavity 410 makes thermal contact with the power motor 100, and the other end extends towards the air duct 300. The heat dissipation cavity 410 is filled with a liquid working fluid. When the power motor 100 operates and generates heat, this heat is transferred to the end of the heat dissipation cavity 410 near the power motor 100, causing the liquid working fluid there to absorb heat and vaporize. The vaporized working fluid flows along the extension direction of the heat dissipation cavity 410. For example, one end of the heat dissipation cavity 410 is in close contact with the heating surface of the power motor 100, and the other end extends into the cold area inside the air duct 300. The liquid working fluid can be R1233ZD(E), Novec7500, Novec 7200, HFO-1336mzz(Z), or other environmentally friendly low-pressure phase change working fluids.

[0032] Thus, when the propeller 200 rotates within the duct 310, it generates an airflow that flows axially along the duct 300. This airflow extends through the heat dissipation cavity 410 to one end of the duct 300, carrying away heat from that location and causing the gaseous working fluid within the heat dissipation cavity 410 to liquefy. The liquefied working fluid then flows back to the end near the power motor 100 under the influence of gravity or surface tension (e.g., a wicking structure), completing a thermal cycle. For example, the airflow generated by the propeller 200 can directly blow against the outer wall of the heat dissipation cavity 410, thereby achieving both cooling and liquefaction of the gaseous working fluid.

[0033] The thermal management device proposed in this application transfers the heat generated by the power motor 100 to the liquid working fluid in the heat dissipation cavity 410, utilizing the phase change of the working fluid to achieve efficient heat absorption. Simultaneously, a portion of the forced airflow generated by the propeller 200 is used to cool the heat dissipation cavity 410, causing the gaseous working fluid to release heat, liquefy, and flow back, forming an efficient thermal cycle. Therefore, this device effectively solves the problem that existing liquid cooling devices cannot meet the heat dissipation requirements of the high-power power motor 100, ensuring the stability and reliability of the power motor 100 under long-term high-load operation, thereby improving the flight safety of the electric aircraft.

[0034] In one embodiment, such as Figures 1-5 As shown, this application further proposes that the supporting heat dissipation structure 400 includes an evaporation section 420 and a supporting tube 430. The evaporation section 420 and the heating end of the power motor 100 are in thermal contact. One end of the supporting tube 430 is fixedly connected to the outer periphery of the evaporation section 420, and the other end is supported and connected to the inner wall of the air duct 300. Multiple supporting tubes 430 are distributed at intervals along the outer periphery of the evaporation section 420. The heat dissipation cavity 410 includes an evaporation cavity 421 and a condensation cavity 431. The evaporation cavity 421 is disposed in the evaporation section 420 and contains a liquid working fluid. At least a portion of the supporting tubes 430 are provided with condensation cavities 431. One end of each condensation cavity 431 is connected to the evaporation cavity 421, and the other end extends toward the inner wall of the air duct 300.

[0035] Specifically, the evaporator 420 is a component in the supporting heat dissipation structure 400 specifically designed for thermally conductive contact with the heating end of the motor 100 and for absorbing heat and vaporizing the internal liquid working fluid. The evaporator 420 is typically designed as a metal structure with a large thermally conductive area and good thermal conductivity, such as copper or aluminum alloy. It contains an evaporation chamber 421 to hold the liquid working fluid. By tightly fitting or integrating the evaporator 420 into the heating area of ​​the motor 100, the heat generated by the motor 100 can be efficiently transferred to the liquid working fluid within the evaporation chamber 421, promoting its rapid evaporation. The shape and size of the evaporator 420 can be optimized according to the specific structure and heating characteristics of the motor 100 to maximize the thermal contact area and heat transfer efficiency.

[0036] The support tube 430 is part of the heat dissipation structure 400. It not only supports the motor 100 mounted on the duct 310 but also performs heat transfer functions. The support tube 430 is typically a hollow structure made of a material with good thermal conductivity, such as a metal tube. One end is fixedly connected to the outer periphery of the evaporator 420, ensuring effective heat transfer from the evaporator 420. The other end is supported and connected to the inner wall of the duct 300, providing structural support and space for the condensation of the gaseous working fluid. Multiple support tubes 430 are spaced apart along the outer periphery of the evaporator 420, which can evenly distribute the support load and provide multiple paths for the flow and condensation of the gaseous working fluid, thereby improving heat dissipation efficiency and structural stability. The cross-sectional shape of the support tube 430 can be circular, elliptical, teardrop-shaped, etc., to adapt to different airflow resistance requirements and structural strength requirements.

[0037] By refining the supporting heat dissipation structure 400 into an evaporation section 420 and a supporting tube 430, and clearly dividing the heat dissipation cavity 410 into an evaporation cavity 421 and a condensation cavity 431, this application achieves zoned management and efficient heat transfer. The evaporation section 420 and its internal evaporation cavity 421 are specifically responsible for efficiently absorbing heat from the power motor 100 and vaporizing the liquid working fluid, while the supporting tube 430 and its internal condensation cavity 431 focus on transporting the gaseous working fluid to areas away from the power motor 100 and efficiently condensing it using the airflow formed by the propeller 200 within the duct 310. This structured design makes the evaporation of the liquid working fluid, the transport and condensation of the gaseous working fluid, and the return flow of the liquid working fluid smoother and more efficient, significantly improving the overall heat dissipation performance and reliability of the thermal management device. The spaced distribution of multiple supporting tubes 430 not only provides stable structural support but also provides multiple channels for the uniform condensation of the gaseous working fluid, further optimizing heat dissipation efficiency.

[0038] In one embodiment, this application further proposes that the support tubes 430 extend radially along the duct 300, and multiple support tubes 430 are evenly spaced along the outer periphery of the evaporator 420. The multiple support tubes 430 are evenly arranged around the outer periphery of the evaporator 420, meaning that the angular intervals between adjacent support tubes 430 are equal. This evenly spaced distribution helps to achieve balanced heat dissipation from the motor 100, avoiding excessive heat concentration in a certain area, thereby ensuring a uniform cooling effect for the entire motor 100. Furthermore, the evenly distributed support tubes 430 also help to balance the forces acting on the motor 100 within the duct 310, further enhancing the structural stability. Considering different heat loads and structural strength requirements, the number of support tubes 430 can be flexibly selected. For example, two oppositely arranged support tubes 430 can be provided to offer basic support and heat dissipation channels, or three, four, or more support tubes 430 can be provided to further improve heat dissipation capacity and structural rigidity. An increase in quantity usually means a larger heat dissipation area and stronger support, but the impact on airflow resistance also needs to be considered. This application is not limited to the quantities listed above, and can be optimized according to specific application scenarios.

[0039] In one embodiment, this application further proposes that the height of the end of the condenser cavity 431 away from the evaporator cavity 421 is greater than the maximum height of the evaporator cavity 421. Specifically, in the heat dissipation support structure 400, the vertical position of the end of the condenser cavity 431 used for condensing the gaseous working fluid away from the evaporator cavity 421 (i.e., the outlet end or lowest point of the condensate return flow) is designed to be higher than the highest point of the evaporator cavity 421 in the vertical direction, which is in thermal contact with the heating end of the power motor 100. This structural configuration aims to utilize gravity to allow the condensed liquid working fluid to flow naturally from the condenser cavity 431 to the evaporator cavity 421. By setting the liquid working fluid outlet end of the condenser cavity 431 above the highest liquid surface of the evaporator cavity 421, an effective gravitational potential energy difference can be formed to drive the liquid working fluid to return. This gravity-assisted reflux mechanism effectively solves the problem of liquid working fluid stagnation in the condensation area, ensuring that the liquid working fluid can be continuously and stably replenished to the evaporation chamber 421, preventing the evaporation chamber 421 from drying out due to insufficient working fluid, thereby maintaining the continuous circulation of liquid working fluid in the heat dissipation chamber 410.

[0040] Specifically, in one embodiment, such as Figures 1-5As shown, this application further proposes defining the support tube 430 with the condenser cavity 431 as the condenser tube body, which extends radially along the duct 300 towards the upper end of the duct 300. Specifically, the support tube 430 with the condenser cavity 431 is explicitly referred to as the condenser tube body for ease of distinction and description. This condenser tube body extends radially along the duct 300, that is, from the evaporator section 420 towards the inner wall of the duct 300. However, its extension direction is not purely horizontal radial, but rather inclined towards the upper end of the duct 300. This means that while extending radially, the end of the condenser tube body furthest from the evaporator cavity 421 has a higher vertical position relative to the end closer to the evaporator cavity 421, thus forming an upward tilt angle. This inclined setting, combined with the feature that the height of the end of the condenser cavity 431 away from the evaporator cavity 421 is greater than the maximum height of the evaporator cavity 421, ensures that the gaseous working fluid in the condenser cavity 431 can flow smoothly upward to the condensation area, and that the liquefied liquid working fluid can flow back to the evaporator cavity 421 efficiently along the inclined direction of the condenser tube body by gravity.

[0041] In one embodiment, such as Figures 1-5 As shown, this application further proposes that multiple condenser tubes are arranged at intervals along the circumference of the evaporator section 420 to form a fan-shaped heat dissipation area, where the central angle A of the heat dissipation area satisfies 15°≤A<180°. Specifically, the multiple condenser tubes being arranged at intervals along the circumference of the evaporator section 420 means that these condenser tubes are arranged around the outer periphery of the evaporator section 420, with a certain gap between adjacent condenser tubes. This interval arrangement helps ensure that each condenser tube can fully contact the airflow generated by the propeller 200, thereby improving heat dissipation efficiency. At the same time, the interval arrangement also avoids the condenser tubes being too dense, which would obstruct airflow and affect the overall heat dissipation performance. This arrangement can be adjusted according to actual heat dissipation requirements and space constraints; for example, a uniform interval arrangement can be used, or a non-uniform interval arrangement can be used according to the heat load distribution of different areas of the power motor 100.

[0042] The fan-shaped heat dissipation area refers to the area occupied by these circumferentially spaced condenser tubes. This fan-shaped area is the main spatial range for heat dissipation by the condenser tubes. The central angle A corresponding to the heat dissipation area satisfies 15°≤A<180°. This central angle A defines the angular range of the fan-shaped heat dissipation area. The 15°≤A constraint ensures that the heat dissipation area has sufficient width to accommodate a sufficient number of condenser tubes and provide the necessary heat dissipation area, thereby guaranteeing basic heat dissipation capacity. If the central angle is too small, it may lead to insufficient heat dissipation area, failing to effectively remove the heat generated by the power motor 100. The A<180° constraint indicates that the heat dissipation area does not cover a semi-circle or larger area around the evaporator section 420. This may take into account factors such as the reflux of the liquid working fluid, structural integration, airflow optimization, or interference with other components.

[0043] In one embodiment, this application further proposes that the liquid working fluid located in the evaporation chamber 421 and the heating surface of the power motor 100 are in contact through a partition wall of the evaporation section 420. The heating surface of the power motor 100 refers to the surface inside the power motor 100 that generates heat and needs to dissipate it, typically the stator winding, rotor, or motor housing. The partition wall of the evaporation section 420 is the physical interface between the evaporation section 420 and the heating surface of the power motor 100, as well as between the evaporation section 420 and the liquid working fluid in the evaporation chamber 421. Its material is typically a metal with good thermal conductivity, such as copper or aluminum alloy, and can be designed with an appropriate thickness to optimize heat transfer efficiency. Partition wall contact means that there is a physical barrier between the liquid working fluid and the heating surface of the power motor 100, namely the partition wall of the evaporation section 420, through which heat is conducted. This contact method avoids direct contact between the liquid working fluid and the heating components of the power motor 100, thereby ensuring electrical insulation and preventing working fluid contamination. The sidewall of the evaporation section 420 serves as a highly efficient heat-conducting interface, which can quickly transfer the heat generated by the power motor 100 to the liquid working fluid in the evaporation chamber 421, promoting its rapid vaporization. This achieves efficient thermal management of the power motor 100 and improves the overall heat dissipation performance and reliability of the device.

[0044] In one embodiment, this application further proposes that the evaporation section 420 is attached to one side of the stator winding of the power motor 100, or that the stator winding of the power motor 100 is at least partially immersed in the liquid working fluid of the evaporation chamber 421. Specifically, the evaporation section 420 is a key component in the supporting heat dissipation structure 400 responsible for absorbing heat and vaporizing the liquid working fluid. In this embodiment, the evaporation section 420 is designed to be closely attached to the stator winding of the power motor 100. By directly attaching the evaporation section 420 to one side of the stator winding, an efficient heat conduction path can be established, allowing the heat generated by the stator winding to be quickly transferred to the liquid working fluid inside the evaporation section 420. This attachment can be achieved in various ways. For example, the evaporation section 420 can adopt a structure that matches the shape of the stator winding, and good thermal contact between the two can be ensured by means of thermally conductive adhesive, thermally conductive pads, or mechanical clamping, thereby minimizing thermal resistance and improving heat transfer efficiency.

[0045] Alternatively, the evaporation chamber 421 is the space inside the evaporation section 420 that contains the liquid working fluid. The liquid working fluid undergoes a phase change and vaporizes after absorbing heat, thereby carrying away the heat. In this embodiment, the stator windings of the motor 100 are designed to be at least partially immersed directly in the liquid working fluid within the evaporation chamber 421. This immersion cooling method provides extremely high heat transfer efficiency because heat can be directly transferred from the surface of the stator windings to the liquid working fluid, avoiding the thermal resistance caused by indirect heat exchange through solid walls. To achieve immersion, the structure of the evaporation chamber 421 needs to be specially designed; for example, a groove or cavity can be formed to accommodate part of the stator windings, ensuring that the liquid working fluid can fully contact the heating surface of the stator windings. This direct contact allows the liquid working fluid to absorb the heat generated by the stator windings more quickly and effectively, thereby achieving a stronger cooling effect.

[0046] In one embodiment, this application further proposes that the air duct 300 is provided with a balancing cavity 320, which extends circumferentially along the air duct 300. The ends of the condenser tube cavities 431 of the multiple condenser tubes, away from the evaporator cavity 421, are respectively connected to the balancing cavity 320. Specifically, the balancing cavity 320 is an annular or arc-shaped cavity disposed inside the air duct 300, extending circumferentially along the air duct 300. The balancing cavity 320 can be an independent annular pipe, an annular groove integrally formed on the inner wall of the air duct 300, or a closed annular space formed on the inner wall of the air duct 300 through additional structures. Its cross-sectional shape can be designed as circular, rectangular, or other shapes suitable for fluid flow according to actual needs. The main function of the balancing chamber 320 is to serve as an intermediate collection point to collect the liquid working fluid returning from multiple condenser chambers 431. It can also balance the uniform distribution of the working fluid in each condenser chamber 431. In addition, when non-condensable gases appear in the condenser chamber 431, the balancing chamber 320 can also serve as a space to store the non-condensable gases, so as to reduce their impact on the condensation effect.

[0047] Through the above technical solution, a circumferentially extending balance chamber 320 is set on the air duct 300, and the ends of the condenser tubes 431 of multiple condenser tubes away from the evaporator chamber 421 are respectively connected to the balance chamber 320, realizing centralized collection and unified reflux of liquid working fluid. When the gaseous working fluid releases heat and liquefies in the condenser tube 431, the liquid working fluid no longer needs to find its own independent reflux path, but instead gathers in the balance chamber 320. As a buffer and collection area, the balance chamber 320 can effectively integrate the liquid working fluid from different condenser tubes 431, avoiding the problems of path complexity and pressure unevenness that may be caused by multiple independent refluxes. This design helps to balance the reflux pressure of each condenser tube 431, ensuring that the liquid working fluid can flow back to the evaporator chamber 421 more smoothly and evenly, thereby improving the working fluid circulation efficiency and heat dissipation performance of the entire thermal management device. Especially under complex operating conditions such as changes in aircraft attitude or vibration, the balance chamber 320 can provide a more stable liquid working fluid reflux environment, ensuring continuous and efficient heat dissipation of the power motor 100.

[0048] In one embodiment, this application further proposes that the above-mentioned supporting heat dissipation structure 400 also includes a branch pipe body 440, one end of which is connected to a condenser pipe body, and the other end is connected to the inner wall of the air duct 300 or an adjacent condenser pipe body. The heat dissipation cavity 410 also includes a branch pipe cavity 441, one end of which is connected to a condenser pipe cavity 431, and the other end is connected to a balance cavity 320 or an adjacent condenser pipe cavity 431.

[0049] The branch pipe body 440 is a tubular component supporting the heat dissipation structure 400, primarily providing mechanical support and serving as a channel for the working fluid. The branch pipe cavity 441 is a cavity located inside the branch pipe body 440 and is a component of the heat dissipation cavity 410. Through the above technical solution, the branch pipe body 440 and the branch pipe cavity 441 provide an additional or optimized connection channel between the condenser cavity 431 and the balance cavity 320. This channel can be designed specifically to guide gaseous or liquid working fluids, effectively avoiding mutual interference between gas and liquid two-phase flows in a single channel. This optimized design significantly improves the transfer efficiency and phase change efficiency of the working fluid inside the thermal management device, thereby improving the heat dissipation performance of the power motor 100 and the overall operational stability of the device. For example, when the branch pipe cavity 441 is mainly used for the transfer of gaseous working fluid, it can reduce the flow resistance of the gaseous working fluid between the condenser cavity 431 and the balance cavity 320, ensuring that the gaseous working fluid can enter the balance cavity 320 more uniformly and quickly, thereby improving the condensation efficiency. When the branch pipe 441 is mainly used for the reflux of liquid working fluid, it can prevent the liquid working fluid from accumulating in the balance chamber 320, ensuring that the liquid working fluid can smoothly return to the evaporation chamber 421, maintaining efficient working fluid circulation, and thus ensuring the continuous and stable heat dissipation effect of the power motor 100. The branch pipe 441 is also the final link supporting the heat dissipation structure 400 to transfer heat to the external fins 450.

[0050] In one embodiment, such as Figures 1-3 As shown, this application further proposes that the branch pipe cavity 441 extends vertically. When the gaseous working fluid in the condenser cavity 431 releases heat and liquefies, the resulting liquid working fluid can fully utilize gravity and flow quickly and smoothly downward into the balance cavity 320 through the vertically extending branch pipe cavity 441, effectively avoiding liquid stagnation and accumulation. This ensures that the condenser cavity 431 can continuously provide a highly efficient condensation surface, maintain good circulation of the liquid working fluid, and thus significantly improve the overall heat dissipation performance and operational stability of the thermal management device. Especially in application scenarios where the device's attitude changes or gravity has a significant impact, it can effectively ensure the stable operation of the power motor 100.

[0051] In another embodiment, such as Figure 4 As shown, the branch lumen 441 extends at an angle relative to the vertical direction. At this time, the angle between the branch lumen 441 and the vertical direction can be 30°, 45°, 60°, etc., which will not be listed here.

[0052] In yet another embodiment, such as Figure 5 As shown, the branch lumen 441 can also be extended along the circumferential direction, in which case the liquid working fluid can also flow naturally by gravity along the extension direction of the branch lumen 441.

[0053] In one embodiment, such as Figures 1-5 As shown, this application further proposes that the supporting heat dissipation structure 400 also includes fins 450, with condenser tubes and branch tubes 440 respectively passing through the fins 450 and in thermally conductive contact with them. Specifically, the fins 450 are structures used to increase the heat exchange surface area, typically made of high thermal conductivity materials, such as aluminum, copper, or their alloys. Their main function is to expand the surface area in contact with the fluid (in this case, the airflow generated by the propeller 200), thereby improving the efficiency of heat transfer from the tube wall to the fluid. The fins 450 can have various geometries, such as flat, corrugated, needle-like, or louvered, and the specific shape can be optimized according to airflow characteristics and space constraints. The condenser tubes and branch tubes 440 respectively pass through the fins 450, meaning that the fins 450 are fixed to the outer surfaces of the condenser tubes and branch tubes 440. This insertion method can be mechanical pressing, tube expansion, welding, brazing, or bonding, etc., to ensure a tight physical connection between the fins 450 and the tube body. In this way, when the gaseous working fluid inside the condenser tube and branch tube 440 condenses and releases heat, the heat can be efficiently transferred to the fins 450. Simultaneously, it makes thermally conductive contact with the fins 450, meaning there is a good heat conduction path between the fins 450 and the condenser tube and branch tube 440. To ensure efficient thermally conductive contact, materials with high thermal conductivity are typically used, and measures are taken at the connection interface to reduce thermal resistance, such as using thermally conductive adhesives, brazing materials, or achieving a tight fit through precise machining. Good thermally conductive contact is crucial for ensuring that heat is effectively transferred from the tube body to the fins 450 and then dissipated into the airflow.

[0054] Furthermore, in one embodiment, this application proposes that the fins 450 be arranged horizontally. A horizontal arrangement of the fins 450 means that the main plane of the fins 450 is parallel to the axis of the duct 300 and parallel to the direction of the airflow flowing along the axial direction of the duct 300 within the duct 310. This arrangement allows the fins 450 to maximize heat exchange with the airflow while minimizing obstruction. Specifically, the fins 450 can be designed as a series of parallel thin plates extending along the axial direction of the duct 300 and making thermal contact with the condenser tube and branch tube 440 passing through it. When the branch tube 441 extends vertically, the horizontally arranged fins 450 will be perpendicular to the branch tube 440, forming a typical finned tube heat exchanger structure, thereby providing sufficient heat exchange area for the condensation of the gaseous working fluid and the reflux of the liquid working fluid.

[0055] However, this is not the only one. In other embodiments, the fins 450 may also be inclined or bent, which will not be listed here.

[0056] In one embodiment, such as Figure 3As shown, this application further proposes an aerodynamic optimization design for the support tube 430. Specifically, when the extension direction of the support tube 430 is not vertical, the upper end of the support tube 430 is provided with an arc-shaped lifting surface 432. Along the direction from the front side to the rear side of the aircraft, the height of the lifting surface 432 first increases and then decreases. This design gives the support tube 430 an airfoil-like profile in the airflow, which can effectively guide the airflow and reduce drag. Here, the lifting surface 432 refers to the region with a certain curvature on the upper surface of the support tube 430, and its height variation trend simulates the cross-sectional characteristics of a typical airfoil from the leading edge to the trailing edge, aiming to optimize the flow state when the airflow passes through the support tube 430.

[0057] When the support tube 430 extends vertically, its two ends are symmetrically arranged, and its cross-section is teardrop-shaped. This teardrop-shaped cross-section is a classic low-drag aerodynamic profile, and its bilateral symmetry ensures good aerodynamic performance even with slight deviations in airflow direction. The teardrop-shaped cross-section, through its smooth transition and gradually tapering tail, effectively prevents airflow separation, thereby significantly reducing pressure drag.

[0058] Through the aforementioned technical solutions, the aerodynamic shape of the support tube 430 is optimized. Whether it's the arc-shaped lifting surface 432 design used when its extension direction is not vertical, or the teardrop-shaped cross-section design used when its extension direction is vertical, both can significantly reduce the aerodynamic drag generated by the support tube 430 in the high-speed airflow within the duct 310. This drag reduction not only reduces the energy consumption required for the propeller 200 to drive the airflow and improves the overall efficiency of the airflow, ensuring that the condenser cavity 431 receives sufficient and stable cooling airflow, thereby improving the heat dissipation performance of the thermal management device. Simultaneously, the optimized aerodynamic shape also helps suppress airflow separation and turbulence generation, reducing vibration and noise caused by airflow disturbances, thereby improving the operational stability and comfort of the aircraft.

[0059] In one embodiment, such as Figure 3 As shown, this application further proposes that the lower end face of the support tube 430 is a plane. When the propeller 200 forms an airflow along the axial direction of the wind tunnel 300 within the duct 310, the lower end face can guide the airflow to pass smoothly, reducing the possibility of airflow separation on the lower surface, thereby reducing the resistance caused by airflow separation.

[0060] In one embodiment, such as Figure 6As shown, this application further proposes that the evaporation chamber 421 includes a reflux channel 422 and a collection chamber 423. Multiple condenser tubes 431 are distributed and connected to the outer periphery of the reflux channel 422. The collection chamber 423 is located at one end of the reflux channel 422 near the power motor 100 and is connected to the reflux channel 422. The collection chamber 423 and the heating end of the power motor 100 are in thermal contact.

[0061] Specifically, the reflux channel 422 is the path within the evaporation chamber 421 used to guide the liquid working fluid back from the condenser chamber 431 to the collecting chamber 423. The reflux channel 422 provides a centralized reflux path for the liquid working fluid, ensuring that it can efficiently return from the condensation area to the evaporation area. The design of the reflux channel 422 can employ different cross-sectional shapes and sizes according to specific structural requirements and working fluid flow rates to optimize fluid resistance and promote uniform distribution of the working fluid. The collecting chamber 423 refers to an area within the evaporation chamber 421 near the heating end of the motor 100, used to collect the liquid working fluid flowing back from the reflux channel 422. This chamber typically has direct thermal contact with the heating end of the motor 100 and is the initial area where the liquid working fluid absorbs heat and begins to evaporate. The design of the collecting chamber 423 should ensure sufficient volume to store the liquid working fluid and provide a sufficiently large heat exchange area to efficiently absorb heat from the motor 100. Its shape and size can be customized according to the shape of the heating surface of the power motor 100 and the heat dissipation requirements. For example, it can be designed as a flat, ring-shaped or grooved shape.

[0062] Multiple condenser chambers 431 are distributed and connected to the outer periphery of the return channel 422. This means that the liquid working fluid returning from the condenser chambers 431 in the support tube 430 no longer directly enters a large evaporation chamber 421, but instead first flows into the return channel 422. This design makes the return path of the liquid working fluid clearer and more focused. The connection between the condenser chambers 431 and the return channel 422 can be a direct open connection or achieved through a transition structure. This distribution and connection method helps to uniformly guide the liquid working fluid collected by multiple condenser chambers 431 to the return channel 422, avoiding disorderly flow of the working fluid in the evaporation chamber 421, thereby improving the return efficiency.

[0063] The collecting chamber 423 is located at one end of the return channel 422 near the power motor 100 and is connected to the return channel 422. This feature clarifies the relative position and functional connection of the collecting chamber 423 within the entire evaporation chamber 421. The collecting chamber 423 is located at the end of the return channel 422, which is the end point of the liquid working fluid return and also the starting point of the evaporation process. Its connection to the return channel 422 ensures that the liquid working fluid returning from the condenser chamber 431 can smoothly enter the collecting chamber 423, providing sufficient liquid working fluid for the subsequent evaporation process. This layout facilitates the formation of a closed working fluid circulation path and ensures that the liquid working fluid evaporates at the point where heat is most needed (i.e., the heating end of the power motor 100).

[0064] Through the above technical solution, the evaporation chamber 421 is subdivided into a reflux channel 422 and a collecting chamber 423, and multiple condensing tubes 431 are connected to the outer periphery of the reflux channel 422. The path of the liquid working fluid flowing back from the condensation area to the evaporation area is clearly planned. The collecting chamber 423 is directly located on the side of the reflux channel 422 near the heating end of the power motor 100 and is in thermal contact with it, ensuring that the refluxed liquid working fluid can be concentrated at the heat source to efficiently absorb heat and vaporize. This structural design optimizes the circulation path of the liquid working fluid, avoiding the problem of local overheating or poor reflux caused by disordered flow of the working fluid in the evaporation chamber 421, thereby significantly improving the overall heat exchange efficiency and reliability of the thermal management device, and ensuring that the power motor 100 can maintain stable performance even under long-term operation.

[0065] In one embodiment, this application further proposes to optimize the reflux channel 422 of the evaporation chamber 421. Specifically, one end of the reflux channel 422 that connects to the collecting chamber 423 is provided with an expansion cavity 426, the flow area of ​​which increases along the direction from the reflux channel 422 to the collecting chamber 423. The expansion cavity 426 is a fluid channel structure whose flow area gradually increases along the fluid flow direction. This design aims to optimize the flow characteristics of the liquid working fluid when it enters the collecting chamber 423 from the reflux channel 422. Specifically, the expansion cavity 426 can adopt a conical, trumpet-shaped, or stepped inner wall structure, so that the liquid working fluid can undergo a smooth deceleration process when entering the collecting chamber 423, thereby effectively reducing fluid impact and turbulence, promoting the stable collection of the liquid working fluid in the collecting chamber 423, and providing a uniform and sufficient liquid phase supply for the subsequent phase change endothermic process.

[0066] In one embodiment, such as Figure 6As shown, this application further proposes that the end of the return channel 422 away from the collecting cavity 423 is provided with a head guide shroud 500, and the cross-sectional area of ​​the head guide shroud 500 decreases along the direction from the collecting cavity 423 to the return channel 422. Correspondingly, the end of the power motor 100 away from the collecting cavity 423 is provided with a tail guide shroud 600, and the cross-sectional area of ​​the tail guide shroud 600 decreases along the direction from the return channel 422 to the collecting cavity 423. In the above-described conical head guide shroud 500 and tail guide shroud 600 design, the conical outer wall is a common streamlined design, and its cross-sectional area gradually changes along a certain direction. Here, the conical outer wall helps to achieve a smooth transition in high-speed airflow, effectively reducing the resistance generated when the airflow passes through the head guide shroud 500 and tail guide shroud 600.

[0067] In one embodiment, such as Figure 6 As shown, this application further proposes that the aforementioned supporting heat dissipation structure 400 also includes a pumping assembly 460, a delivery pipe 470, and a baffle plate 480. The lower end of the baffle plate 480 is sealed to the inner wall of the collecting cavity 423, dividing the collecting cavity 423 into a first cavity 424 near the return channel 422 and a second cavity 425 near the power motor 100. A vapor channel 490 is formed between the upper end of the baffle plate 480 and the inner wall of the collecting cavity 423. The liquid working fluid returning from the condenser cavity 431 can enter the first cavity 424 through the lower region of the return channel 422. One end of the delivery pipe 470 is immersed in the liquid working fluid in the first cavity 424, and the other end crosses the vapor channel 490 and extends into the second cavity 425. The pumping assembly 460 can transport the liquid working fluid from the first chamber 424 to the second chamber 425 through the delivery pipe 470. The liquid working fluid in the second chamber 425 can absorb heat and vaporize into a gaseous working fluid and enter the condenser chamber 431 through the upper region of the vapor channel 490 and the return channel 422.

[0068] Specifically, the pumping assembly 460 is used to actively transport the liquid working medium from the first chamber 424 to the second chamber 425. It can be implemented in various forms; for example, it can be a micro-mechanical pump, such as a centrifugal pump or gear pump, driven by a motor to achieve forced circulation of the liquid working medium; it can also be an electromagnetic pump, using electromagnetic force to drive the flow of the conductive liquid working medium; or it can be another microfluidic pumping device such as a piezoelectric pump. The pumping assembly 460 is designed to overcome gravity, surface tension, or flow resistance to ensure a stable and sufficient supply of liquid working medium to the heating area of ​​the power motor 100. The delivery pipe 470 is a channel for guiding the liquid working medium from the first chamber 424 to the second chamber 425. One end of the conveying pipe 470 is immersed in the liquid working fluid in the first chamber 424 to absorb the returned liquid working fluid; the other end crosses the vapor channel 490 and extends into the second chamber 425, directly delivering the liquid working fluid transported by the pumping assembly 460 to the second chamber 425, ensuring that the liquid working fluid can effectively wet the heating surface of the power motor 100. The material of the conveying pipe 470 is usually selected to be compatible with the working fluid and corrosion-resistant, such as stainless steel or a specific polymer. The baffle plate 480 is disposed inside the collecting chamber 423, and its main function is to divide the collecting chamber 423 into two independent areas: the first chamber 424 and the second chamber 425. The lower end of the baffle plate 480 is sealed to the inner wall of the collecting chamber 423 to ensure the isolation of the first chamber 424 and the second chamber 425 at the liquid working fluid level. The upper end of the baffle plate 480 is spaced from the inner wall of the collecting chamber 423, thereby forming a vapor channel 490, allowing the gaseous working fluid to flow upward from the second chamber 425. The first chamber 424 is the portion of the collecting chamber 423 near the return channel 422, primarily used to collect the liquid working fluid returning from the condenser chamber 431. The liquid working fluid enters the first chamber 424 through the lower region of the return channel 422. The bottom of the first chamber 424 is lower than the bottom of the return channel 422, allowing the liquid working fluid to form a pool here, providing a source of liquid working fluid for the pumping assembly 460. The second chamber 425 is the portion of the collecting chamber 423 near the heating end of the power motor 100 and is the main evaporation area. After the pumping assembly 460 delivers the liquid working fluid to the second chamber 425, the liquid working fluid makes thermal contact with the heating end of the power motor 100, absorbing heat and vaporizing. The design of the second chamber 425 should ensure that the liquid working fluid can fully cover the heating surface of the power motor 100 to achieve efficient heat transfer. The vapor channel 490 is the gap formed between the upper end of the baffle plate 480 and the inner wall of the collecting chamber 423, serving as the outlet for the gaseous working fluid to flow from the second chamber 425 to the upper region of the return channel 422. The design of this channel should ensure that the gaseous working fluid can smoothly leave the second chamber 425, avoiding excessive local pressure, while also preventing the liquid working fluid from flowing back through this channel. After the gaseous working fluid in the condenser chamber 431 releases heat and liquefies, the liquid working fluid flows along the lower region of the return channel 422 under the action of gravity or surface tension, eventually collecting in the first chamber 424.The pumping assembly 460 draws liquid working fluid from the first chamber 424 and forces it to the second chamber 425 through the delivery pipe 470. After the liquid working fluid in the second chamber 425 absorbs heat and vaporizes, the resulting gaseous working fluid flows upward through the vapor channel 490 and enters the upper region of the return channel 422, and then flows to the condenser chamber 431, completing the circulation of the gaseous working fluid.

[0069] By introducing a pumping assembly 460, a delivery pipe 470, and a baffle plate 480 into the supporting heat dissipation structure 400, and by dividing the collecting chamber 423, this application enables forced circulation of the liquid working fluid. Specifically, the condensed liquid working fluid first collects in the first chamber 424, and is then actively transported by the pumping assembly 460 to the second chamber 425 through the delivery pipe 470. The second chamber 425 is in close contact with the heating end of the power motor 100, ensuring that the liquid working fluid can continuously and fully wet the heating surface, thereby efficiently absorbing the heat generated by the power motor 100 and vaporizing it. The resulting gaseous working fluid then flows smoothly to the condensing chamber 431 through the vapor channel 490 and the upper area of ​​the return channel 422 for exothermic liquefaction. This active pumping circulation method effectively solves the problems of insufficient liquid working fluid supply and drying of the evaporation area that may occur in traditional passive return systems when facing high heat flux density or complex postures, significantly improving the heat dissipation efficiency and operational stability of the thermal management device. It ensures that heat can be continuously and efficiently transferred from the power motor 100, thereby guaranteeing the reliable operation of the power motor 100 under various operating conditions. Furthermore, the above scheme effectively achieves the separate flow of the gaseous and liquid working fluids. On the one hand, it reduces heat transfer between the two; on the other hand, since the gaseous and liquid working fluids flow in opposite directions, this reduces the flow resistance of each fluid separately, prevents turbulence, and improves the circulation efficiency of the working fluid.

[0070] Specifically, in one embodiment, this application further proposes that the vertical height of the steam channel 490 is greater than the vertical height of the stator winding of the power motor 100. Specifically, the height difference between the vertical height of the steam channel 490 and the vertical height of the stator winding of the power motor 100 is between 3mm and 5mm. The height difference between the vertical height of the steam channel 490 and the vertical height of the stator winding of the power motor 100 is a key parameter for ensuring the gas-liquid separation effect. Limiting this height difference to the range of 3mm-5mm provides an optimized gas-liquid separation space, ensuring the purity of the gaseous working fluid while also considering the compactness of the device and the smoothness of airflow, thereby achieving efficient and stable thermal management.

[0071] In one embodiment, the power motor 100, the second chamber 425, the first chamber 424, and the return channel 422 are arranged sequentially along the axial direction of the air duct 300. By arranging the power motor 100, the second chamber 425, the first chamber 424, and the return channel 422 sequentially along the axial direction of the air duct 300, this application effectively solves the problem of achieving efficient working fluid circulation and integrated heat dissipation within a limited space. This axially sequential arrangement allows the liquid working fluid to be transported from the first chamber 424 to the second chamber 425 by the pumping assembly 460 for evaporation, while the gaseous working fluid enters the condenser chamber 431 through the vapor channel 490 and the upper region of the return channel 422. The condensed liquid working fluid then returns to the first chamber 424 through the lower region of the return channel 422, thus optimizing and shortening the entire circulation path. This compact series layout not only maximizes the use of the axial space inside the air duct 300 and reduces the connection length and fluid resistance between components, but also improves the circulation efficiency of the working fluid and the overall heat dissipation performance of the thermal management device. At the same time, this structure facilitates the integration and manufacturing of the device, reduces complexity, and helps to achieve lightweight design.

[0072] In one embodiment, this application further proposes that the flow area of ​​the vapor channel 490 is greater than or equal to the flow area of ​​the return channel 422, and the flow area of ​​the return channel 422 is greater than or equal to the sum of the flow areas of the multiple condensing chambers 431. Through the above technical solution, this application optimizes the flow path of the gaseous working fluid inside the thermal management device. First, the flow area of ​​the vapor channel 490 is greater than or equal to the flow area of ​​the return channel 422, effectively avoiding excessive local resistance when the gaseous working fluid is discharged from the second chamber 425, ensuring that the gaseous working fluid can smoothly enter the return channel 422. Second, the flow area of ​​the return channel 422 is greater than or equal to the sum of the flow areas of the multiple condensing chambers 431, ensuring that the return channel 422 can fully carry and evenly distribute the gaseous working fluid to each condensing chamber 431, avoiding uneven heat dissipation efficiency or local overheating problems in the condensing chambers 431 due to insufficient gaseous working fluid supply. This reasonable matching of flow area significantly reduces the flow resistance of the gaseous working fluid throughout the phase change cycle, promotes the rapid evaporation of the liquid working fluid and the effective condensation of the gaseous working fluid, thereby improving the overall heat transfer efficiency and stability of the thermal management device and ensuring the efficient heat dissipation of the power motor 100 during long-term operation.

[0073] In one embodiment, this application further proposes that the pumping assembly 460 is a magnetic coupling pump. This magnetic coupling pump includes a magnetic actuator and a magnetic impeller assembly. The magnetic actuator is directly mounted to the output end of the power motor 100 or mounted to the output end of the power motor 100 via a transmission assembly, enabling the power motor 100 to drive the magnetic actuator to rotate. The magnetic impeller assembly is installed inside the delivery pipe 470. When the power motor 100 is operating, the rotating magnetic field of the magnetic actuator drives the magnetic impeller assembly to rotate synchronously. The centrifugal force generated by the magnetic impeller assembly pumps the liquid working fluid in the first chamber 424 into the delivery pipe 470 and then delivers it to the second chamber 425.

[0074] Specifically, a magnetic coupling pump is a non-contact pump that transmits torque via magnetic force. There is no mechanical connection between the driving and driven parts; instead, they are coupled through a magnetic field. This design effectively prevents liquid leakage and improves the system's sealing and reliability. A magnetic coupling pump typically consists of an external magnetic actuator and an internal magnetic impeller assembly, separated by a non-magnetic isolation sleeve, thus achieving leak-free fluid delivery. Its advantages include compact structure, smooth operation, low maintenance costs, and adaptability to various working media. The magnetic actuator is the external driving part of the magnetic coupling pump, typically containing a set of permanent magnets or electromagnetic coils to generate a rotating magnetic field. The magnetic impeller assembly is the driven part, installed inside the delivery pipe 470. It also contains permanent magnets or magnetic materials and rotates synchronously with the magnetic actuator under the influence of the rotating magnetic field, thereby driving the impeller to rotate and perform work on the fluid. This separate design completely isolates the pumped medium from the external drive mechanism, avoiding wear and leakage problems associated with dynamic seals.

[0075] The magnetic actuator is connected to the output end of the power motor 100, enabling direct drive of the power motor 100. Direct installation means the magnetic actuator is directly connected to the shaft of the power motor 100, for example, via a key, spline, or threaded connection, allowing the rotational motion of the power motor 100 to be directly transmitted to the magnetic actuator. Installation via a transmission assembly means that one or more transmission components, such as gears, belts, or couplings, are placed between the output end of the power motor 100 and the magnetic actuator to transmit or adjust torque and speed. This integrated drive method fully utilizes the existing power output of the power motor 100, eliminating the need for an additional independent drive motor, thus simplifying the system structure and reducing overall weight and energy consumption. The power motor 100, as the core power source of the entire device, uses the rotational motion of its output shaft to drive the propeller 200 to generate airflow. Furthermore, the rotational power of the power motor 100 is cleverly utilized to drive the magnetic actuator. This means the magnetic actuator is connected to the shaft of the power motor 100 or its transmission mechanism; when the power motor 100 operates, its rotational torque is synchronously transmitted to the magnetic actuator, causing it to rotate accordingly. This design enables the reuse of the power source, avoiding the complexity of configuring a separate drive mechanism for the pumping assembly 460.

[0076] The magnetic impeller assembly is the core working component of the magnetic coupling pump. It contains an impeller that performs work on the liquid working medium. Installing it inside the delivery pipe 470 ensures that the liquid working medium is pumped within a closed flow channel, avoiding contact with the external environment and further enhancing the system's sealing and reliability. The delivery pipe 470, serving as the liquid working medium's transport path, makes efficient use of its internal space, allowing the magnetic impeller assembly to be compactly integrated into the fluid circuit. When the power motor 100 starts and drives the magnetic actuator to rotate, the actuator generates a rotating magnetic field. This rotating magnetic field penetrates the wall of the delivery pipe 470 and magnetically couples with the magnets on the magnetic impeller assembly installed inside the pipe. Due to the attraction and repulsion of the magnetic forces, the magnetic impeller assembly rotates synchronously with the rotating magnetic field of the actuator. This non-contact synchronous rotation ensures smooth power transmission and avoids mechanical wear and leakage. During rotation, the blades of the magnetic impeller assembly exert a force on the surrounding liquid working medium, generating centrifugal force. This centrifugal force draws the liquid working fluid in the first chamber 424 into the center of the impeller, where it is accelerated by the impeller's rotation and ultimately ejected at a high pressure and flow rate into the delivery pipe 470. Through the delivery pipe 470, this pumped liquid working fluid is effectively transported to the second chamber 425, thus completing the circulation process of the liquid working fluid from the condensation reflux area to the evaporation area, ensuring a continuous supply of liquid working fluid in the evaporation chamber 421.

[0077] Through the above technical solution, the pumping component 460 is specifically configured as a magnetically coupled pump, and the magnetic actuator is driven directly or through a transmission component using the output end of the power motor 100, thus achieving an integrated design of the pumping component 460 and the power motor 100. This design eliminates the need for an additional independent drive source for the circulating pumping of the liquid working fluid, effectively reducing the overall weight and volume of the device and simplifying the structure. The non-contact transmission characteristics of the magnetically coupled pump avoid the dynamic seal leakage problem of traditional mechanical pumps, significantly improving the system's sealing performance and operational reliability. When the power motor 100 is working, its rotating magnetic field can synchronously drive the magnetic impeller assembly, and the resulting centrifugal force efficiently pumps the liquid working fluid in the first chamber 424 to the second chamber 425, ensuring a stable supply of liquid working fluid in the evaporation chamber 421, thereby maintaining the continuous and efficient operation of the thermal management device, which is particularly suitable for applications with high requirements for weight, volume, and reliability.

[0078] However, this is not the only option. In other embodiments, the pumping assembly 460 may also be a conventional liquid pump, with the power cord of the liquid pump sealed through the inner wall of the heat dissipation cavity 410.

[0079] Specifically, in one embodiment, the pumping assembly 460 includes a controller, a liquid pump, and a liquid level sensor. The liquid level sensor is disposed in either the first chamber 424 or the second chamber 425. When the liquid level sensor is disposed in the first chamber 424 and measures that the liquid level of the working medium in the first chamber 424 is higher than a first preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first chamber 424 to the second chamber 425 through the delivery pipe 470. Alternatively, when the liquid level sensor is disposed in the second chamber 425 and measures that the liquid level of the working medium in the second chamber 425 is lower than a second preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first chamber 424 to the second chamber 425 through the delivery pipe 470. In this way, the pumping assembly 460 operates independently and can unidirectionally transport the liquid working medium between the first chamber 424 and the second chamber 425 according to the actual liquid level.

[0080] In one embodiment, this application further proposes that the supporting heat dissipation structure 400 is disposed on the front side of the aircraft, and the propeller 200 is disposed on the rear side of the aircraft. The propeller 200 is a thrust-generating component that drives the aircraft forward through high-speed rotation. Distributing it at the rear of the aircraft, i.e., after the supporting heat dissipation structure 400, ensures that the airflow generated by the propeller 200 first passes through the supporting heat dissipation structure 400 during operation. This series arrangement effectively utilizes the thrust of the propeller 200 to form a directional cooling airflow, providing condensation conditions for the gaseous working fluid within the heat dissipation cavity 410, thereby optimizing the overall heat dissipation efficiency of the thermal management device. Simultaneously, placing the propeller 200 at the rear also contributes to the aerodynamic layout of the aircraft, reducing interference with the front structure of the aircraft and lowering overall aerodynamic drag.

[0081] By employing the aforementioned technical solution, positioning the heat dissipation support structure 400 at the front of the aircraft effectively utilizes the oncoming airflow generated during the aircraft's forward movement to provide a highly efficient cooling medium for the structure, thereby enhancing the condensation efficiency of the gaseous working fluid within the heat dissipation cavity 410. Simultaneously, positioning the propeller 200 at the rear of the aircraft allows the thrust generated by the propeller 200 to flow smoothly through the front heat dissipation support structure 400, forming a directional and powerful cooling airflow, further optimizing the heat dissipation performance of the thermal management device. This front-rear layout not only facilitates airflow organization and utilization, reducing aerodynamic drag, but also allows for a more compact and efficient integration of the power motor 100 and its heat dissipation components with the propeller 200, thereby improving the overall performance and reliability of the aircraft.

[0082] In one embodiment, this application further proposes that the distance B between the supporting heat dissipation structure 400 and the propeller 200 satisfies 1mm≤B≤20mm, preferably 2mm≤B≤10mm. The distance B refers to the axial distance between the supporting heat dissipation structure 400 and the propeller 200. Setting this distance is crucial to ensuring that the airflow generated by the propeller 200 can effectively and uniformly flow through the supporting heat dissipation structure 400, thereby carrying away heat. Specifically, when the distance B is set within the range of 1mm to 20mm, it can effectively balance the airflow organization, heat dissipation efficiency, and structural compactness, forming an effective negative pressure and making the cooling airflow more uniform. If the distance B is less than 1mm, the rotation of the propeller 200 may cause aerodynamic interference to the supporting heat dissipation structure 400, or even physical interference, affecting the efficiency and structural safety of the propeller 200, and may also restrict the full development of airflow, leading to uneven heat dissipation. Conversely, if the spacing B is greater than 20mm, firstly, it increases the axial dimension of the device, which is not conducive to compact design; secondly, because the air resistance of the supporting heat dissipation structure 400 is relatively large, the airflow generated by the suction passes through other parts of the duct more often, weakening the cooling effect. Preferably, setting the spacing B within the range of 2mm to 10mm can further optimize the above balance. Within this preferred range, the airflow generated by the propeller 200 can flow through the supporting heat dissipation structure 400 at a higher speed and with better uniformity, ensuring efficient heat transfer, while avoiding interference problems that may occur if the spacing is too close, and contributing to a more compact overall layout.

[0083] In one embodiment, this application further proposes that both the air inlet and outlet of the duct 310 are non-circular, while the cross-section of the section where the propeller 200 is located in the duct 310 is circular. Specifically, the non-circular shape of the air inlet and outlet of the duct 310 means that the cross-sectional shape of the duct 310 in the air inlet and outlet areas is not circular; for example, it can be elliptical, rectangular, flat, airfoil-shaped, or other irregular geometric shapes. This design allows the duct 310 to better integrate with the external aerodynamic shape of the aircraft or other carrier in the air inlet and outlet areas, thereby effectively reducing aerodynamic drag and improving overall flight efficiency. For example, the air inlet can be designed as a flat shape flush with the fuselage or wing edge to reduce the frontal area; the outlet can be designed as a shape that matches the tail structure to optimize the wake. In addition, the non-circular shape can also provide greater flexibility for the arrangement of internal components or meet specific structural strength requirements. Meanwhile, the section of the duct 310 containing the propeller 200 has a perfectly circular cross-section, meaning that the cross-section of the duct 310 in the region where the propeller 200 is located is a standard circle. When the propeller 200 operates within the circular cross-section of the duct 310, it achieves optimal aerodynamic efficiency. The circular duct 310 ensures that airflow passes uniformly through the propeller 200 blades, reducing vortices and airflow separation, thereby maximizing the thrust output and energy conversion efficiency of the propeller 200. Simultaneously, the circular cross-section facilitates clearance control between the propeller 200 and the duct 310 wall, further optimizing airflow guidance.

[0084] In one embodiment, this application further proposes that when the wall thickness of the thermal management device is greater than or equal to 3 mm, the sidewall of the thermal management device is a hollow or porous structure. This condition limits the application scenarios of this technical solution. When the sidewall thickness of the thermal management device reaches or exceeds 3 mm, the increased weight and potential thermal performance problems caused by the solid structure become particularly prominent, thus requiring special structural design for optimization. For cases with smaller wall thicknesses, a solid structure may still be an acceptable or more economical choice.

[0085] In one embodiment, this application further proposes an aircraft that includes the thermal management device described in any of the above embodiments. Specifically, an aircraft refers to a machine capable of flying within or outside the atmosphere, overcoming gravity by generating lift or thrust. Aircraft can be classified into various types according to their purpose, structure, and flight principle, such as unmanned aerial vehicles (UAVs), multi-rotor aircraft, fixed-wing aircraft, electric vertical takeoff and landing (eVTOL) aircraft, or hybrid-powered aircraft. In this embodiment, the aircraft integrates the aforementioned thermal management device to achieve effective thermal management of its power motor 100. An aircraft typically consists of a fuselage, a power system, a control system, and a payload, among which the power system is the key part for the aircraft to achieve flight, and the power motor 100, as the core component of the power system, directly affects the performance and reliability of the aircraft due to its operating temperature.

[0086] By integrating the aforementioned thermal management devices into the aircraft, the aircraft achieves continuous and efficient heat dissipation for the power motor 100. This allows the power motor 100 to maintain its optimal operating temperature range under high load and long-term operation conditions, effectively avoiding performance degradation, efficiency reduction, and even malfunctions caused by motor overheating. Therefore, the aircraft can achieve longer endurance, greater payload capacity, and higher flight speeds, significantly improving its overall performance and operational reliability. Furthermore, efficient thermal management also helps extend the service life of the power motor 100, reduces maintenance costs, and enables compact design and high power density integration of the aircraft.

[0087] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0088] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the scope of protection of this application should be determined by the appended claims.

[0089] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application 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, and therefore should not be construed as a limitation of this application.

[0090] 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 technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0091] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0092] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0093] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0094] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the specification of this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

Claims

1. A thermal management device, characterized by, The utility model relates to a kind of power motor and its support and heat dissipation structure, including: Power motor (100); Propeller (200), it is connected to the output end of the power motor (100), and the power motor (100) can drive the rotation of the propeller (200); Duct (310) is provided along the axial direction of wind tube (300) through, and the wind tube (300) is set on the outer circumferential side of the power motor (100) and the propeller (200) by the duct (310); And, Support heat dissipation structure (400), the power motor (100) is installed in the inner wall of the duct (310) by the support heat dissipation structure (400); The support heat dissipation structure (400) is provided with heat dissipation cavity (410), one end of the heat dissipation cavity (410) is in thermal contact with the power motor (100), the other end extends towards the direction close to the wind tube (300), and the heat dissipation cavity (410) has liquid working medium, liquid working medium can absorb heat and vaporize and flow along the extension direction of the heat dissipation cavity (410), and the propeller (200) can form airflow flowing along the axial direction of the wind tube (300) in the duct (310), so that gaseous working medium in the heat dissipation cavity (410) can be liquefied and backflow to the end close to the power motor (100).

2. The thermal management device of claim 1, wherein, The support heat dissipation structure (400) includes evaporation part (420) and support pipe body (430), the evaporation part (420) is in thermal contact with the heating end of the power motor (100), one end of the support pipe body (430) is fixedly connected to the outer circumferential side of the evaporation part (420), and the other end is supported and connected to the inner side wall of the wind tube (300), and a plurality of support pipe bodies (430) are distributed along the outer circumferential direction of the evaporation part (420) at intervals; The heat dissipation cavity (410) includes evaporation cavity (421) and condensation pipe cavity (431), the evaporation cavity (421) is provided in the evaporation part (420), the evaporation cavity (421) has liquid working medium, at least part of the support pipe body (430) is provided with the condensation pipe cavity (431), and one end of each condensation pipe cavity (431) is communicated with the evaporation cavity (421), and the other end extends towards the direction close to the inner wall of the wind tube (300).

3. The thermal management device of claim 2, wherein, The setting height of the condensation pipe cavity (431) away from one end of the evaporation cavity (421) is greater than the maximum setting height of the evaporation cavity (421).

4. The thermal management device of claim 3, wherein, The support pipe body (430) provided with the condensation pipe cavity (431) is defined as condensation pipe body, and the condensation pipe body extends along the radial direction of the wind tube (300) towards the direction close to the upper end of the wind tube (300); A plurality of condensation pipe bodies are arranged at intervals along the circumferential direction of the evaporation part (420) to form a fan-shaped heat dissipation area, and the corresponding central angle A of the heat dissipation area satisfies 15°≤A<180°.

5. The thermal management device of claim 4, wherein, The air duct (300) is provided with a balance cavity (320) extending along the circumference of the air duct (300), and a plurality of the condensing pipe cavities (431) are respectively communicated with the balance cavity (320) away from one end of the evaporation cavity (421); The support heat dissipation structure (400) further comprises a branch pipe body (440), one end of the branch pipe body (440) is connected with the condensing pipe body, and the other end is connected with the inner wall of the air duct (300) or the adjacent condensing pipe body, the heat dissipation cavity (410) further comprises a branch pipe cavity (441), the branch pipe cavity (441) is arranged in the branch pipe body (440), one end of the branch pipe cavity (441) is communicated with the condensing pipe cavity (431), and the other end is communicated with the balance cavity (320) or the adjacent condensing pipe cavity (431).

6. The thermal management device of claim 2, wherein, The liquid working medium in the evaporation cavity (421) and the heating surface of the power motor (100) are in contact through the side wall partition of the evaporation part (420); The evaporation part (420) is attached to one side of the stator winding of the power motor (100); or the stator winding of the power motor (100) is at least partially immersed in the liquid working medium in the evaporation cavity (421).

7. The thermal management device of claim 2, wherein, When the extension direction of the support pipe body (430) is a non-vertical direction, the upper end of the support pipe body (430) is provided with an arc-shaped lifting surface (432), and along the direction from the front side of the aircraft to the rear side of the aircraft, the height of the lifting surface (432) increases first and then decreases; When the extension direction of the support pipe body (430) is a vertical direction, the two side ends of the support pipe body (430) are symmetrically arranged, and the cross section of the support pipe body (430) is in the shape of a water droplet.

8. The thermal management device of claim 2, wherein, The evaporation cavity (421) comprises a reflux channel (422) and a collection cavity (423), a plurality of the condensing pipe cavities (431) are distributed and communicated with the outer circumferential side of the reflux channel (422), the collection cavity (423) is arranged at one end of the reflux channel (422) close to the power motor (100) and is communicated with the reflux channel (422), and the collection cavity (423) is in heat-conducting contact with the heating end of the power motor (100); One end of the reflux channel (422) communicated with the collection cavity (423) is provided with an expanding cavity (426), and along the direction from the reflux channel (422) to the collection cavity (423), the flow area of the expanding cavity (426) increases.

9. The thermal management device of claim 8, wherein, The support heat dissipation structure (400) further comprises a pumping assembly (460), a conveying pipe (470) and a liquid blocking plate (480), the lower end of the liquid blocking plate (480) is sealingly connected to the inner wall of the collection cavity (423), and the collection cavity (423) is divided into a first cavity (424) close to the reflux channel (422) and a second cavity (425) close to the power motor (100), the upper end of the liquid blocking plate (480) and the inner wall of the collection cavity (423) are arranged at intervals to form a vapor channel (490); The liquid working medium flowing back through the condensing tube cavity (431) can enter the first cavity (424) through the lower side area of the backflow channel (422), one end of the delivery tube (470) is immersed in the liquid working medium in the first cavity (424), the other end crosses the vapor channel (490) and extends into the second cavity (425), the pumping assembly (460) can deliver the liquid working medium from the first cavity (424) to the second cavity (425) through the delivery tube (470), and the liquid working medium in the second cavity (425) can be gasified into gaseous working medium by absorbing heat and enter the condensing tube cavity (431) through the vapor channel (490) and the upper side area of the backflow channel (422).

10. The thermal management device of claim 9, wherein, The flow area of the vapor channel (490) is greater than or equal to the flow area of the backflow channel (422), and the flow area of the backflow channel (422) is greater than or equal to the sum of the flow areas of the plurality of condensing tube cavities (431).

11. The thermal management device of claim 9, wherein, The pumping assembly (460) is a magnetic coupling pump, which comprises a magnetic driver and a magnetic impeller assembly, the magnetic driver is directly installed on the output end of the power motor (100) or is installed on the output end of the power motor (100) through a transmission assembly, the power motor (100) can drive the magnetic driver to rotate, and the magnetic impeller assembly is installed inside the delivery tube (470), when the power motor (100) works, the rotating magnetic field of the magnetic driver can drive the magnetic impeller assembly to rotate synchronously, and the centrifugal force generated by the magnetic impeller assembly can pump the liquid working medium in the first cavity (424) into the delivery tube (470) and deliver it to the second cavity (425); Alternatively, the pumping assembly (460) comprises a controller, a liquid pump and a liquid level sensor, the liquid level sensor is arranged in the first cavity (424) or the second cavity (425); when the liquid level sensor is arranged in the first cavity (424) and measures that the liquid level of the liquid working medium in the first cavity (424) is higher than a first preset liquid level, the controller can control the liquid pump to start working and deliver the liquid working medium from the first cavity (424) to the second cavity (425) through the delivery tube (470); or, when the liquid level sensor is arranged in the second cavity (425) and measures that the liquid level of the liquid working medium in the second cavity (425) is lower than a second preset liquid level, the controller can control the liquid pump to start working and deliver the liquid working medium from the first cavity (424) to the second cavity (425) through the delivery tube (470).

12. The thermal management device of claim 1, wherein, The support heat dissipation structure (400) is arranged on the front side of the aircraft, and the propeller (200) is arranged on the rear side of the aircraft.

13. An aircraft characterized by, The thermal management device according to any one of claims 1-12. The thermal management device according to any one of claims 1-12.

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