Thermal management device and aircraft

Abstract

The application relates to a heat management device and an aircraft, the heat management device comprising at least two rotor assemblies and at least one windward cooling structure, each windward cooling structure being connected to two adjacent rotor assemblies respectively, each rotor assembly comprising a power motor, a propeller, a wind tube and a supporting heat dissipation structure. The power motor can drive the propeller to rotate. The wind tube is sleeved on the outer circumferential side of the power motor and the propeller through a duct. The power motor is installed on the inner wall of the duct through the supporting heat dissipation structure. The windward cooling structure is provided with a cooling cavity, one end of a heat dissipation cavity of the supporting heat dissipation structure is in heat conduction contact with the power motor, and the other end extends towards the direction close to the wind tube and is communicated with the cooling cavity. The heat management device and the aircraft provided by the application can solve the problems that the existing liquid cooling device is difficult to meet the heat dissipation requirement of the power motor, and the large number of liquid cooling devices is not conducive to the light weight of the aircraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of flight devices, in particular to a thermal management device and an aircraft. BACKGROUND

[0002] In the technical field of electric aircraft (for example, electric vertical take-off and landing aircraft), the heat dissipation of power motors is often very large, and therefore, the heat dissipation of power motors (especially stator windings) becomes a focus. In the current technical solution, the heat dissipation of power motors is mainly achieved by contact heat transfer between motor housings and liquid cooling plates or by oil immersion. However, with the substantial increase in power motor power, the current liquid cooling device cannot meet the heat dissipation needs of power motors. If the heat of power motors cannot be removed in time, the power motors may be damaged, and even the flight safety of the aircraft may be directly affected.

[0003] Especially when the number of power motors and propellers of the aircraft is large, the number of liquid cooling devices corresponding to the power motors is also large, which is obviously not conducive to the lightweight design of the aircraft. SUMMARY

[0004] Therefore, it is necessary to provide a thermal management device and an aircraft to solve the problems that the current liquid cooling device cannot meet the heat dissipation needs of power motors and the large number of liquid cooling devices is not conducive to the lightweight design of the aircraft.

[0005] The thermal management device provided by the present application comprises at least two rotor assemblies and at least one windward cooling structure. Each windward cooling structure is connected to two adjacent rotor assemblies. Each rotor assembly comprises a power motor, a propeller, a wind tube, and a support heat dissipation structure. The propeller is connected to the output end of the power motor, and the power motor can drive the propeller to rotate. The wind tube is provided with a duct along the axial direction of the wind tube, and 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 inner wall of the duct through the support heat dissipation structure, and the support heat dissipation structure is provided with a heat dissipation cavity. The windward cooling structure is provided with a cooling 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 wind tube and communicates with the cooling cavity. The heat dissipation cavity contains a liquid working medium. The liquid working medium can absorb heat to vaporize and flow to the cooling cavity along the extension direction of the heat dissipation cavity. 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 liquefies by releasing heat. When the aircraft is in a flight state, the external airflow can pass through the outer wall surface of the cooling cavity, so that the gaseous working medium in the cooling cavity liquefies by releasing heat. The gaseous working medium in the heat dissipation cavity and the cooling cavity can be condensed and flow back to the end of the heat dissipation cavity close to the power motor.

[0006] In one of the embodiments, the axes of the plurality of rotor assemblies are arranged in parallel, and the plurality of rotor assemblies are arranged side by side along a direction perpendicular to the axes of the plurality of rotor assemblies, and the two ends of the windward cooling structure are respectively fixedly connected to adjacent rotor assemblies.

[0007] In one of the embodiments, the support heat dissipation structure comprises an evaporation part and a support pipe body, the evaporation part is in thermal contact with the heat generating end of the power motor, one end of the support pipe body is fixedly connected to the outer circumferential side of the evaporation part, and the other end is supported and connected to the inner side wall of the wind tube, and a plurality of support pipe bodies are distributed along the outer circumferential direction of the evaporation part. The heat dissipation cavity comprises an evaporation cavity and a condensation pipe cavity, the evaporation cavity is arranged in the evaporation part, the evaporation cavity contains liquid working medium, and at least part of the support pipe bodies are provided with the condensation pipe cavity, one end of each condensation pipe cavity is respectively communicated with the evaporation cavity, and the other end extends towards the direction close to the inner wall of the wind tube and is communicated with the cooling cavity.

[0008] In one of the embodiments, the setting height of the end of the condensation pipe cavity away from the evaporation cavity is greater than or equal to the maximum setting height of the evaporation cavity. The support pipe body provided with the condensation pipe cavity is defined as a condensation pipe body, and the condensation pipe body extends along the radial direction of the wind tube towards the direction close to the upper end of the wind tube.

[0009] In one of the embodiments, the wind tube is provided with a first balance cavity, the first balance cavity extends along the circumferential direction of the wind tube, and the ends of the condensation pipe cavities of the plurality of condensation pipe bodies away from the evaporation cavity are respectively communicated with the first balance cavity. The windward cooling structure comprises a connecting pipe body and a cooling pipe body, the two ends of the connecting pipe body are respectively connected to the outer walls of adjacent wind tubes, one end of the cooling pipe body is connected to the outer wall of the wind tube, and the other end is connected to the connecting pipe body or adjacent cooling pipe body. The cooling cavity comprises a second balance cavity and a branch cavity, the second balance cavity is arranged in the connecting pipe body, and the branch cavity is arranged in the corresponding cooling pipe body, one end of the branch cavity is communicated with the first balance cavity, and the other end is communicated with the second balance cavity or adjacent branch cavity.

[0010] In one of the embodiments, the two first balance cavities of adjacent wind tubes and the second balance cavities of the connecting pipe bodies are sequentially communicated and form an annular channel structure surrounding the outer circumferential side of the branch cavity.

[0011] In one of the embodiments, the heat management device further comprises a deflector group, the deflector group is arranged on the leeward side of the windward cooling structure, the deflector group, the windward cooling structure and the outer walls of adjacent wind tubes surround to form a flow guide cavity, and the side walls of adjacent wind tubes are respectively provided with flow guide openings communicated with the flow guide cavity. When the propeller rotates, the airflow on the windward side of the windward cooling structure can enter the duct in sequence through the windward cooling structure, the flow guide cavity and the flow guide opening.

[0012] In one of the embodiments, the deflector set comprises an outer plate body and an inner plate body, the peripheral side of the outer plate body is sealingly connected to the connecting pipe body and the peripheral side of the adjacent air duct, the inner plate body is arranged on the side of the outer plate body close to the windward cooling structure, and the inner plate body is provided with a first deflector surface and a second deflector surface respectively arranged towards the adjacent deflector opening, so that the airflow can enter the adjacent deflector opening through the first deflector surface and the second deflector surface respectively.

[0013] In one of the embodiments, the flow area of the deflector openings communicating with the same deflector cavity is equal, and the sum of the flow areas of the deflector openings communicating with the same deflector cavity is greater than or equal to the flow area of the windward cooling structure.

[0014] In one of the embodiments, the evaporation cavity comprises a reflux channel and a collection cavity, a plurality of condenser tube cavities are distributed and connected to the peripheral side of the reflux channel, the collection cavity is arranged at one end of the reflux channel close to the power motor and is connected to the reflux channel, and the collection cavity and the heat generating end of the power motor are in heat conduction contact. The end of the reflux channel connected to the collection cavity is provided with an expanding cavity, and the flow area of the expanding cavity shows an increasing trend along the direction from the reflux channel to the collection cavity.

[0015] In one of the embodiments, the support heat dissipation structure further comprises a pumping assembly, a delivery pipe and a liquid blocking plate, the lower end of the liquid blocking plate is sealingly connected to the inner wall of the collection cavity, and the collection cavity is divided into a first cavity close to the reflux channel and a second cavity close to the power motor, and the upper end of the liquid blocking plate and the inner wall of the collection cavity are spaced apart to form a vapor channel. The liquid working medium refluxed by the condenser tube cavity can enter the first cavity through the lower side area of the reflux channel, one end of the delivery pipe is immersed in the liquid working medium in the first cavity, the other end crosses the vapor channel and extends into the second cavity, the pumping assembly can deliver the liquid working medium from the first cavity to the second cavity through the delivery pipe, and the liquid working medium in the second cavity can be heated and vaporized into gaseous working medium and enter the condenser tube cavity through the vapor channel and the upper side area of the reflux channel.

[0016] In one of the embodiments, the pumping assembly is a magnetic coupling pump, the magnetic coupling pump comprises a magnetic driver and a magnetic impeller assembly, the magnetic driver is directly installed on the output end of the power motor or is installed on the output end of the power motor through a transmission assembly, the power motor can drive the magnetic driver to rotate, and the magnetic impeller assembly is installed inside the delivery pipe. When the power motor is working, 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 into the delivery pipe and deliver it to the second cavity.

[0017] In one of the embodiments, the pumping assembly comprises a controller, a liquid pump and a liquid level sensor, the liquid level sensor is arranged in the first cavity or the second cavity; when the liquid level sensor is arranged in the first cavity and detects that the liquid level of the liquid working medium in the first cavity is higher than the first preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first cavity to the second cavity through the delivery pipe; or when the liquid level sensor is arranged in the second cavity and detects that the liquid level of the liquid working medium in the second cavity is lower than the second preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first cavity to the second cavity through the delivery pipe.

[0018] In one of the embodiments, the support heat dissipation structure is arranged at the front side of the rotor assembly, and the propeller is arranged at the rear side of the rotor assembly.

[0019] The application further provides an aircraft comprising the heat management device according to any one of the embodiments.

[0020] Compared with the prior art, the heat management device and the aircraft provided by the application combine the heat dissipation of the power motor with the support heat dissipation structure of the rotor assembly and the windward cooling structure of the aircraft, utilize the phase change heat transfer characteristics of the liquid working medium, and combine the internal airflow generated by the propeller and the external airflow during flight to perform cooling, thereby solving the problem of insufficient heat dissipation capacity of the conventional liquid cooling device. Meanwhile, the integrated design reduces the number of independent heat dissipation components, which helps to realize the lightweight of the aircraft and improves the overall performance and safety of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative effort.

[0022] Figure 1 Structure diagram of the heat management device according to an embodiment of the application Figure 1 ;

[0023] Figure 2 Structure diagram of the heat management device according to an embodiment of the application Figure 2 ;

[0024] Figure 3 Sectional view of the heat management device according to an embodiment of the application

[0025] Figure 4 Partial three-dimensional view of the heat management device according to an embodiment of the application

[0026] Figure 5Partial sectional view of a heat management device according to an embodiment of the present application;

[0027] Figure 6 Partial structural view of a heat management device according to an embodiment of the present application;

[0028] Figure 7 Sectional view of a heat management device according to an embodiment of the present application.

[0029] 1000, rotor assembly; 100, power motor; 200, propeller; 300, wind tube; 310, duct; 320, first balance cavity; 330, guide opening; 400, support heat dissipation structure; 410, heat dissipation cavity; 420, evaporation part; 421, evaporation cavity; 422, return channel; 423, collection cavity; 424, first cavity; 425, second cavity; 426, flared cavity; 430, support pipe body; 431, condensation pipe cavity; 450, fin; 460, pumping assembly; 470, delivery pipe; 480, liquid blocking plate; 490, vapor channel; 500, head fairing; 600, tail fairing; 2000, windward cooling structure; 2100, cooling cavity; 2200, connecting pipe body; 2210, second balance cavity; 2300, cooling pipe body; 2310, branch cavity; 3000, guide plate set; 3100, guide cavity; 3200, outer plate body; 3300, inner plate body; 3310, first guide surface; 3320, second guide surface. DETAILED DESCRIPTION

[0030] Current electric aircraft power motor heat dissipation mainly relies on liquid cooling devices, but as the power of the motor increases, the existing liquid cooling devices cannot meet the heat dissipation demand, which may limit the output power of the motor and even damage it, affecting flight safety. In addition, the number of liquid cooling devices is large under multi-motor configuration, which is not conducive to the lightweight design of the aircraft.

[0031] Please refer to Figures 1-7 To solve the above problems, the present application provides a heat management device, which includes at least two rotor assemblies 1000 and at least one windward cooling structure 2000, each windward cooling structure 2000 is connected to two adjacent rotor assemblies 1000, and the rotor assembly 1000 provides lift or thrust for the aircraft. The rotor assembly 1000 provided in the embodiment can be arranged in any relative position relationship, such as series, parallel or staggered arrangement. The windward cooling structure 2000 can be connected to the adjacent rotor assembly 1000 by a flexible or rigid connecting piece, such as by welding, bolt connection, adhesion or lapping.

[0032] And each rotor assembly 1000 includes a power motor 100, a propeller 200, a wind barrel 300, a support heat dissipation structure 400, the propeller 200 is connected to the output end of the power motor 100, the power motor 100 can drive the propeller 200 to rotate, the wind barrel 300 is provided with a duct 310 penetrating along the axial direction of itself, the wind barrel 300 is sleeved on the outer circumferential side of the power motor 100 and the propeller 200 through the duct 310, the power motor 100 is installed on the inner wall of the duct 310 through the support heat dissipation structure 400, and the support heat dissipation structure 400 is provided with a heat dissipation cavity 410.

[0033] The wind barrel 300 is in a cylindrical structure, is provided with the duct 310 inside, is used for coating the power motor 100 and the propeller 200, and guides the airflow. The support heat dissipation structure 400 is configured to support the power motor 100 and simultaneously realize heat dissipation of the power motor 100. The liquid working medium is a kind of fluid that can absorb heat and vaporize at a specific temperature and condense back to flow after cooling, is used for heat transfer, and can be R1233ZD (E), Novec 7500, Novec 7200, HFO-1336mzz (Z) or other environmentally friendly low-pressure phase change working medium.

[0034] The windward cooling structure 2000 is provided with a cooling cavity 2100, 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 barrel 300 and communicates with the cooling cavity 2100, the heat dissipation cavity 410 has the liquid working medium inside, the liquid working medium can absorb heat and vaporize and flow to the cooling cavity 2100 along the extension direction of the heat dissipation cavity 410, the propeller 200 can form an airflow flowing along the axial direction of the wind barrel 300 in the duct 310, so as to cool the gaseous working medium in the heat dissipation cavity 410, and when the aircraft is in a flight state, the external airflow can pass through the outer wall surface of the cooling cavity 2100 to cool the gaseous working medium in the cooling cavity 2100, and the gaseous working medium in the heat dissipation cavity 410 and the cooling cavity 2100 can condense back to the end close to the power motor 100 of the heat dissipation cavity 410. The gaseous working medium in the heat dissipation cavity 410 and the cooling cavity 2100 condenses into liquid working medium after cooling. The condensed liquid working medium can rely on the action of gravity and flow back to the end close to the power motor 100 of the heat dissipation cavity 410 along the inclined channel or flow guide structure inside the heat dissipation cavity 410 and the cooling cavity 2100. It can also be achieved by setting a liquid collecting groove at the bottom of the system and utilizing capillary action or gravity to realize the circulation of the working medium.

[0035] The heat management device provided in the embodiment solves the problem of insufficient heat dissipation capacity of the traditional liquid cooling device by combining the heat dissipation of the power motor 100 with the support heat dissipation structure 400 of the rotor assembly 1000 and the windward cooling structure 2000 of the aircraft, utilizing the phase change heat transfer characteristics of the liquid working medium, and combining the internal airflow generated by the propeller 200 and the external airflow during flight. At the same time, the integrated design reduces the number of independent heat dissipation components, helps to realize the lightweight of the aircraft, and improves the overall performance and safety of the aircraft.

[0036] In an embodiment, as shown in Figures 1-3 The heat management device provided in the present application is provided, wherein the axes of the plurality of rotor assemblies 1000 are arranged in parallel, and the plurality of rotor assemblies 1000 are arranged side by side along the direction perpendicular to the axes thereof, and the two ends of the windward cooling structure 2000 are respectively fixedly connected to the adjacent rotor assemblies 1000.

[0037] Specifically, the parallel arrangement of the axes of the plurality of rotor assemblies 1000 means that the rotation axes of the rotor assemblies 1000 are kept in the same direction, for example, in a multi-rotor aircraft, the thrust directions of all the propellers 200 are kept consistent, thereby simplifying the flight control and ensuring the stability of the thrust output. This parallel layout also helps to realize the compactness and streamline design of the overall structure. The side-by-side arrangement of the plurality of rotor assemblies 1000 along the direction perpendicular to the axes thereof means that the rotor assemblies 1000 are arranged in the direction perpendicular to the axes thereof in space, for example, in a horizontal direction. For example, in a multi-rotor aircraft, the rotor assemblies 1000 can be arranged in a straight line or a circular array. This layout is conducive to the connection of the windward cooling structure 2000 between the adjacent rotor assemblies 1000, and optimizes the floor area and aerodynamic shape of the entire device. The two ends of the windward cooling structure 2000 are respectively fixedly connected to the adjacent rotor assemblies 1000, which means that a stable and immovable connection is formed between the windward cooling structure 2000 and the adjacent rotor assemblies 1000. This connection can be achieved by various mechanical means, such as bolt connection, riveting, welding, and strong bonding, to ensure the reliability of the connection and the integrity of the structure. Through the fixed connection, the windward cooling structure 2000 can be firmly kept in the predetermined position, effectively capturing the external airflow for cooling, and possibly serving as a structural member to enhance the rigidity of the entire device.

[0038] Through the above technical solutions, the axes of the plurality of rotor assemblies 1000 are arranged in parallel and arranged side by side along the direction perpendicular to the axes thereof, and the two ends of the windward cooling structure 2000 are fixedly connected to the adjacent rotor assemblies 1000, thereby realizing the compactness and integration of the heat management device. This specific layout ensures that the windward cooling structure 2000 can be optimally exposed to the external airflow during flight, thereby maximizing its cooling efficiency.

[0039] In an embodiment, as shown in FIG. 4A, the application further proposes that the support heat dissipation structure 400 comprises an evaporation part 420 and a support pipe body 430, the evaporation part 420 is in thermal contact with the heat generating end of the power motor 100, and the support pipe body 430 is fixedly connected to the outer circumferential side of the evaporation part 420 at one end and is supportingly connected to the inner side wall of the air duct 300 at the other end, and a plurality of support pipe bodies 430 are distributed along the outer circumferential direction of the evaporation part 420. The heat dissipation cavity 410 comprises an evaporation cavity 421 and a condensation pipe cavity 431, the evaporation cavity 421 is arranged in the evaporation part 420, the evaporation cavity 421 is filled with liquid working medium, and at least part of the support pipe bodies 430 are provided with the condensation pipe cavity 431, one end of each condensation pipe cavity 431 is respectively communicated with the evaporation cavity 421, and the other end extends towards the direction close to the inner wall of the air duct 300 and is communicated with the cooling cavity 2100. Figure 3 Figure 6 Specifically, the evaporation part 420 is the core component of the support heat dissipation structure 400 responsible for receiving heat and vaporizing working medium, which is usually made of high thermal conductivity material and can be designed in various shapes to maximize the contact area with the power motor 100 and the internal heat exchange area. The evaporation part 420 is in thermal contact with the heat generating end of the power motor 100, which can be achieved by direct contact, using thermal pads or thermal gels, etc., aiming to minimize thermal resistance and ensure that the heat generated by the power motor 100 can be efficiently and quickly transferred to the evaporation part 420. The support pipe body 430 has the dual functions of mechanical support and heat transfer. One end is firmly fixed to the outer circumferential side of the evaporation part 420, and the other end is supportingly connected to the inner side wall of the air duct 300, thereby stably fixing the power motor 100 and the evaporation part 420 inside the air duct 300 and bearing the mechanical load during operation. A plurality of support pipe bodies 430 are distributed along the outer circumferential direction of the evaporation part 420, which not only provides uniform mechanical support but also helps to reduce the obstruction to the airflow in the duct 310. The heat dissipation cavity 410 is subdivided into the evaporation cavity 421 and the condensation pipe cavity 431. The evaporation cavity 421 is arranged inside the evaporation part 420 and is the main area where the liquid working medium absorbs heat and vaporizes into gaseous working medium. The evaporation cavity 421 is filled with liquid working medium, which undergoes phase change after absorbing heat. The condensation pipe cavity 431 is arranged inside at least part of the support pipe bodies 430 and serves as a transmission channel for the gaseous working medium flowing out of the evaporation cavity 421. One end of each condensation pipe cavity 431 is communicated with the evaporation cavity 421, ensuring the smooth entry of gaseous working medium. The other end of the condensation pipe cavity 431 extends towards the direction close to the inner wall of the air duct 300 and is finally communicated with the cooling cavity 2100, enabling the gaseous working medium to be cooled by the airflow in the duct 310 or external airflow during flow, thereby realizing condensation.

[0040] Specifically, the evaporation part 420 is the core component of the support heat dissipation structure 400 responsible for receiving heat and vaporizing working medium, which is usually made of high thermal conductivity material and can be designed in various shapes to maximize the contact area with the power motor 100 and the internal heat exchange area. The evaporation part 420 is in thermal contact with the heat generating end of the power motor 100, which can be achieved by direct contact, using thermal pads or thermal gels, etc., aiming to minimize thermal resistance and ensure that the heat generated by the power motor 100 can be efficiently and quickly transferred to the evaporation part 420. The support pipe body 430 has the dual functions of mechanical support and heat transfer. One end is firmly fixed to the outer circumferential side of the evaporation part 420, and the other end is supportingly connected to the inner side wall of the air duct 300, thereby stably fixing the power motor 100 and the evaporation part 420 inside the air duct 300 and bearing the mechanical load during operation. A plurality of support pipe bodies 430 are distributed along the outer circumferential direction of the evaporation part 420, which not only provides uniform mechanical support but also helps to reduce the obstruction to the airflow in the duct 310. The heat dissipation cavity 410 is subdivided into the evaporation cavity 421 and the condensation pipe cavity 431. The evaporation cavity 421 is arranged inside the evaporation part 420 and is the main area where the liquid working medium absorbs heat and vaporizes into gaseous working medium. The evaporation cavity 421 is filled with liquid working medium, which undergoes phase change after absorbing heat. The condensation pipe cavity 431 is arranged inside at least part of the support pipe bodies 430 and serves as a transmission channel for the gaseous working medium flowing out of the evaporation cavity 421. One end of each condensation pipe cavity 431 is communicated with the evaporation cavity 421, ensuring the smooth entry of gaseous working medium. The other end of the condensation pipe cavity 431 extends towards the direction close to the inner wall of the air duct 300 and is finally communicated with the cooling cavity 2100, enabling the gaseous working medium to be cooled by the airflow in the duct 310 or external airflow during flow, thereby realizing condensation.

[0041] ​In an embodiment, the present application further proposes that the support tubes 430 in the support heat dissipation structure 400 extend along the radial direction of the air duct 300, and a plurality of support tubes 430 are uniformly distributed along the circumferential direction of the evaporation section 420, and the number of support tubes 430 can be 2, 3, 4 or more.

[0042] In an embodiment, the present application further proposes that the height of the condensation tube cavity 431 away from one end of the evaporation cavity 421 is greater than or equal to the maximum height of the evaporation cavity 421.

[0043] Specifically, the above technical features refer to the vertical height position of the condensation tube cavity 431 away from one end of the evaporation cavity 421 (usually the outlet or upper region of the condensation tube cavity 431) in the heat management device, which is higher than the highest vertical height position of the evaporation cavity 421 (where the horizontally arranged condensation tube cavity 431 only serves as a liquid return channel). The evaporation cavity 421 is provided in the evaporation section 420, which is the area where the liquid working medium absorbs heat from the power machine 100 and vaporizes, while the condensation tube cavity 431 is provided in the support tube 430, which is the area where the gaseous working medium releases heat and condenses into liquid working medium. By setting this height difference, the use of gravity can ensure that the liquid working medium condensed in the condensation tube cavity 431 can naturally and smoothly flow back to the evaporation cavity 421 along the direction of gravity. For example, the support tube 430 (where the condensation tube cavity 431 is provided) can be designed to extend upwardly from the evaporation section 420 to the inner wall of the air duct 300, or the overall structural layout can be such that the condensation region of the condensation tube cavity 431 is higher than the liquid surface of the evaporation cavity 421 in the vertical direction.

[0044] In an embodiment, the present application further proposes that the support tube 430 provided with the condensation tube cavity 431 is defined as a condensation tube, wherein the condensation tube is a specific definition of the support tube 430 in the support heat dissipation structure 400, specifically referring to those support tubes 430 with the condensation tube cavity 431 inside. The condensation tube is usually made of high thermal conductivity material to facilitate heat exchange between the gaseous working medium and the external airflow or the wind-facing cooling structure 2000, thereby achieving efficient condensation. Moreover, the condensation tube extends along the radial direction of the air duct 300 towards the direction close to the upper end of the air duct 300. This extension can be a straight upward inclination or an upward extension with a certain curvature. The core is to ensure that the outlet end of the condensation tube cavity 431 is higher than the liquid surface of the evaporation cavity 421, thereby providing a downward gravitational potential difference for the condensed working medium, which is beneficial for the condensed working medium to flow back to the evaporation cavity 421 under the action of gravity. At the same time, the radial extension layout helps the condensation tube to better utilize the airflow inside the air duct 300 for cooling, or to exchange heat with the external wind-facing cooling structure 2000.

[0045] In an embodiment, the application further proposes that a plurality of condensing tube bodies are arranged along the circumference of the evaporation portion 420 to form a fan-shaped heat dissipation area, and the corresponding central angle A of the heat dissipation area satisfies 15°≤A<180°.

[0046] The corresponding central angle A of the heat dissipation area refers to the included angle formed by the condensing tube bodies connecting the two side edges of the fan-shaped heat dissipation area from the center point of the evaporation portion 420. This angle defines the distribution range of the condensing tube bodies in the circumferential direction. The range of 15°≤A<180° defines the minimum and maximum angles of the fan-shaped heat dissipation area. The minimum angle of 15° ensures that a certain number of condensing tube bodies are involved in heat dissipation, avoiding the condensing tube bodies being too concentrated in one point, thereby ensuring the basic heat dissipation area and efficiency. The maximum angle less than 180° means that the condensing tube bodies will not completely cover more than half of the evaporation portion 420, mainly allowing them to be distributed in the upper area of the evaporation portion 420, avoiding the formation of dead angles or reduced efficiency of the airflow in the excessively large covered area.

[0047] In an embodiment, the application further proposes that the liquid working medium located in the evaporation cavity 421 and the heat generating surface of the power motor 100 are in contact through the side wall partition of the evaporation portion 420.

[0048] Specifically, the liquid working medium in the evaporation cavity 421 and the heat generating surface of the power motor 100 are in contact through the side wall partition, that is, the liquid working medium does not directly contact the heat generating surface of the power motor 100, but transfers heat through the side wall of the evaporation portion 420. This design can effectively isolate the liquid working medium from the electrical part of the power motor 100, avoiding electrical faults caused by working medium leakage or electrical conductivity, while ensuring that heat can be efficiently conducted from the power motor 100 to the side wall of the evaporation portion 420, and then to the liquid working medium in the evaporation cavity 421. The side wall of the evaporation portion 420 is usually made of materials with excellent heat conduction performance, such as copper, aluminum alloy, etc., and its thickness can be optimized according to actual needs to maximize the reduction of thermal resistance while ensuring structural strength.

[0049] In addition, the liquid level of the liquid working medium in the evaporation cavity 421 is designed to be higher than the highest point of the heat generating surface of the power motor 100. This means that when the thermal management device is working, all the heat generating surfaces of the power motor 100, or at least the main heat generating area, can be completely immersed in the liquid working medium. This full immersion cooling method can maximize the contact area between the heat generating surface of the power motor 100 and the liquid working medium, thereby fully utilizing the high heat absorption characteristics of the liquid working medium in the boiling phase change process. By precisely controlling the filling amount of the liquid working medium and the structural design of the evaporation cavity 421, it can be ensured that the liquid level always covers the highest heat generating point of the power motor 100 in different working postures.

[0050] Specifically, in an embodiment, the application further proposes that the evaporation part 420 is attached to one side of the stator winding of the power motor 100. Alternatively, the stator winding of the power motor 100 is at least partially immersed in the liquid working medium in the evaporation cavity 421.

[0051] The evaporation part 420 is closely "attached" to one side of the stator winding, aiming to minimize the thermal contact resistance between the two. In specific implementation, the shape of the evaporation part 420 can be designed to match the geometry of the stator winding, for example, if the stator winding is cylindrical, the evaporation part 420 can be designed as a shell with corresponding curvature. The attachment method can include but is not limited to filling and bonding with thermal conductive glue or thermal conductive gasket to ensure good heat conduction. Alternatively, the evaporation part 420 is firmly pressed against the surface of the stator winding by mechanical fasteners (such as bolts, clamps) to achieve close contact. This close fit can ensure that the heat generated by the stator winding can be efficiently and quickly transferred to the liquid working medium inside the evaporation part 420.

[0052] On the other hand, "immersion" means that part of the stator winding of the power motor 100 is directly in contact with the liquid working medium in the evaporation cavity 421. In order to achieve this scheme, the structure of the evaporation cavity 421 needs to be adjusted so that it can accommodate part of the stator winding. For example, the evaporation cavity 421 can be designed as a ring-shaped or U-shaped groove, and the bottom or side of the stator winding can extend into the groove and be completely covered by the liquid working medium. In this case, the selected liquid working medium must have good electrical insulation performance to avoid short circuiting or corrosion of the stator winding of the power motor 100. Common dielectric liquids, such as certain fluorocarbons, are suitable choices. This direct contact method allows the heat generated by the stator winding to be directly transferred to the liquid working medium through boiling heat transfer, and the latent heat of phase change of the liquid working medium is used for efficient heat dissipation.

[0053] Through the above technical solutions, the heat transfer efficiency of the stator winding of the power motor 100 is significantly improved.

[0054] In an embodiment, as Figure 3As shown, the application further proposes that the wind tube 300 is provided with a first balance cavity 320 extending along the circumference of the wind tube 300, and the condensing tube cavities 431 of the plurality of condensing tube bodies are respectively connected to the first balance cavity 320 away from one end of the evaporation cavity 421. The windward cooling structure 2000 includes a connecting tube body 2200 and a cooling tube body 2300, both ends of the connecting tube body 2200 are respectively connected to the outer walls of adjacent wind tubes 300 and are in communication with the first balance cavity 320, and one end of the cooling tube body 2300 is connected to the outer wall of the wind tube 300, and the other end is connected to the connecting tube body 2200 or the adjacent cooling tube body 2300. The cooling cavity 2100 includes a second balance cavity 2210 and a branch cavity 2310, the second balance cavity 2210 is arranged in the connecting tube body 2200, and the branch cavity 2310 is arranged in the corresponding cooling tube body 2300. One end of the branch cavity 2310 is in communication with the first balance cavity 320, and the other end is in communication with the second balance cavity 2210 or the adjacent branch cavity 2310.

[0055] Specifically, the first balance cavity 320 is an annular or approximately annular channel arranged inside or outside the wind tube 300, which mainly serves as a collection point and balance point for the condensing tube cavities 431. When the gaseous working medium in the plurality of condensing tube cavities 431 condenses into liquid working medium, these liquid working media will be collected into the first balance cavity 320. The circumferential extension design of the first balance cavity 320 helps to balance the pressure between the plurality of condensing tube cavities 431, ensuring that the condensed working medium can flow back uniformly and smoothly, avoiding the problem of local blockage or poor backflow. The first balance cavity 320 can adopt a hollow annular structure, and its inner wall or outer wall is integrated with the wind tube 300 or connected through welding, clamping or other means.

[0056] The connecting tube body 2200 and the cooling tube body 2300 together constitute the main part of the windward cooling structure 2000. The connecting tube body 2200 is mainly responsible for connecting the outer walls of two adjacent wind tubes 300 to form a main channel spanning between the rotor assemblies 1000. The cooling tube body 2300 can be led out from the outer wall of the wind tube 300 and connected to the connecting tube body 2200 or the adjacent cooling tube body 2300, thereby forming a more complex cooling network. These tube bodies are provided with cooling cavities 2100 inside, which are the places where the working medium exchanges heat and flows. The connecting tube body 2200 and the cooling tube body 2300 can be made of metal materials with good thermal conductivity, such as aluminum alloy or copper alloy, to facilitate the cooling of the working medium inside by the external airflow. Its cross-sectional shape can be designed as circular, oval or special-shaped according to the requirements of structural strength and fluid resistance.

[0057] The cooling cavity 2100 is composed of the second balance cavity 2210 and the branch cavity 2310. The second balance cavity 2210 is arranged inside the connecting pipe body 2200 as a collection and distribution center of the working medium inside the connecting pipe body 2200, which is connected with a plurality of branch cavities 2310 and forms communication with the cooling cavities 2100 of the adjacent rotor assemblies 1000. The branch cavity 2310 is arranged inside the corresponding cooling pipe body 2300, one end of which is communicated with the first balance cavity 320 to receive the gaseous working medium from the condensing pipe cavity 431, and the other end is communicated with the second balance cavity 2210 or the adjacent branch cavity 2310 to deliver the gaseous working medium to the second balance cavity 2210 or the further cooling path. This design enables the gaseous working medium to flow from each condensing pipe cavity 431 through the first balance cavity 320, the branch cavity 2310, and finally to the second balance cavity 2210, forming a complete circulation path. The internal structure of the second balance cavity 2210 and the branch cavity 2310 can be provided with a turbulence structure to enhance the flow and heat exchange efficiency of the working medium.

[0058] Through the above technical solution, the first balance cavity 320 can effectively distribute the gaseous working medium from the plurality of condensing pipe cavities 431 and achieve pressure balance of the working medium between different condensing pipe cavities 431, avoiding the problem of uneven flow resistance or low backflow efficiency caused by directly connecting the single condensing pipe cavity 431 to the cooling cavity 2100. At the same time, the windward cooling structure 2000 forms a structured cooling network through the connecting pipe body 2200 and the cooling pipe body 2300, and the second balance cavity 2210 and the branch cavity 2310 inside work cooperatively, not only providing a smooth circulation path for the gaseous working medium, but also enabling the entire windward cooling structure 2000 to more efficiently utilize external airflow for heat exchange. This design ensures that the gaseous working medium can continuously and stably flow from the heat dissipation cavity 410 to the cooling cavity 2100 and efficiently backflow to the evaporation cavity 421 after cooling, thereby significantly improving the overall heat dissipation efficiency and system stability of the thermal management device when multiple rotor assemblies 1000 work cooperatively, effectively solving the problems of poor working medium circulation and uneven heat exchange.

[0059] In an embodiment, the two first balance cavities 320 of adjacent wind drums 300 and the second balance cavity 2210 of the connecting pipe body 2200 are sequentially communicated and form an annular channel structure surrounding the outer circumferential side of the branch cavity 2310.

[0060] Specifically, in the thermal management device, first balancing chambers 320 are respectively provided on the air ducts 300 of two adjacent rotor assemblies 1000. These first balancing chambers 320 serve as collection points for gaseous working fluid collected from the condenser chambers 431 of their respective rotor assemblies 1000. Simultaneously, a second balancing chamber 2210 is provided inside the connecting pipe 2200, serving as the main gaseous working fluid channel in the air-cooling structure 2000. By sequentially connecting these two first balancing chambers 320 with the second balancing chamber 2210 of the connecting pipe 2200, a continuous fluid passage is formed. This connection method ensures that gaseous working fluid from different rotor assemblies 1000 can collect and enter the main body of the air-cooling structure 2000. This sequentially connected structure is not a simple linear connection, but rather forms a ring-shaped channel. The ring-shaped channel structure spatially surrounds the branch chambers 2310 in the air-cooling structure 2000. Branch chamber 2310 is a channel inside cooling tube 2300, responsible for transporting the gaseous working fluid from the first balance chamber 320 to the second balance chamber 2210 for cooling. The existence of the annular channel structure means that the gaseous working fluid can circulate or redistribute within this annular channel, thereby providing a uniform inlet or outlet environment for branch chamber 2310. This annular layout helps balance the pressure and flow rate between different branch chambers 2310, ensuring that the gaseous working fluid can flow more evenly through each branch chamber 2310, thereby improving the overall cooling efficiency.

[0061] In one embodiment, such as Figures 4-7 As shown, this application further proposes that the thermal management device also includes a guide plate assembly 3000, which is disposed on the leeward side of the windward cooling structure 2000. The guide plate assembly 3000, the windward cooling structure 2000, and the outer wall of the adjacent air duct 300 form a guide cavity 3100. Furthermore, the side walls of the adjacent air duct 300 are respectively provided with guide ports 330 that communicate with the guide cavity 3100. When the propeller 200 rotates, the airflow on the windward side of the windward cooling structure 2000 can sequentially enter the duct 310 through the windward cooling structure 2000, the guide cavity 3100, and the guide port 330.

[0062] The flow guide plate group 3000 is a structure for guiding airflow, typically composed of one or more plate-like components. Its main function is to optimize the flow path of the airflow, reducing resistance, turbulence or energy loss when the airflow passes through a certain area, thereby improving the utilization efficiency of the airflow. The flow guide plate group 3000 is arranged on the leeward side of the windward cooling structure 2000, i.e. the side after the airflow flows through the windward cooling structure 2000. This layout ensures that the flow guide plate group 3000 effectively captures and guides the airflow that has undergone heat exchange with the windward cooling structure 2000, avoiding the disordered diffusion of the airflow after leaving the cooling structure. At the same time, this arrangement also avoids the direct location of the flow guide plate group 3000 on the windward side, thereby reducing the obstruction to the initial windward airflow, ensuring that the windward cooling structure 2000 can fully utilize the external airflow for cooling. The flow guide cavity 3100 is a semi-closed space formed by the flow guide plate group 3000, the windward cooling structure 2000 and the outer wall of the adjacent wind tunnel 300. The function of the flow guide cavity 3100 is to serve as an intermediate transition area for the airflow flowing from the windward cooling structure 2000 to the duct 310. Through the concentration and guidance of the flow guide cavity 3100, the airflow can be effectively converged and oriented, providing a stable and uniform flow field for subsequent entry into the duct 310. The geometric shape and internal structure of the flow guide cavity 3100 can be optimized according to the characteristics of the airflow, such as using smooth transition curves to minimize airflow separation and pressure loss. The flow guide port 330 is an opening arranged on the side wall of the adjacent wind tunnel 300, which connects the flow guide cavity 3100 and the duct 310. These flow guide ports 330 are the final channels for the airflow to enter the duct 310 from the flow guide cavity 3100. The design of the flow guide port 330 should take into account the angle and speed of the airflow entering the duct 310, to ensure that the airflow can effectively blend with the airflow generated by the propeller 200 in the duct 310, reducing the impact on the working efficiency of the propeller 200. The flow guide port 330 can be designed in different shapes, such as rectangular, oval or irregular, and its size and distribution can be adjusted according to actual needs to optimize the effect of airflow introduction. When the aircraft is in flight or the propeller 200 is rotating, the external airflow first flows through the windward cooling structure 2000 to cool the gaseous working medium inside it. Subsequently, the cooled or disturbed airflow is captured by the flow guide plate group 3000 and guided into the flow guide cavity 3100. In the flow guide cavity 3100, the airflow is further converged and oriented, and finally smoothly enters the duct 310 of the wind tunnel 300 through the flow guide port 330, merging with the airflow generated by the propeller 200. This sequential path design ensures the effective utilization of the airflow, both cooling the cooling cavity 2100 and efficiently introducing the airflow into the duct 310 to support the operation of the propeller 200.

[0063] By the above technical solution, the windward side of the windward cooling structure 2000 is additionally provided with the flow guide plate group 3000, which is jointly surrounded with the windward cooling structure 2000 and the outer wall of the adjacent air duct 300 to form a flow guide cavity 3100, and the flow guide opening 330 is arranged on the side wall of the air duct 300, thereby providing a clear and controlled flow path for the airflow. When the propeller 200 rotates, the airflow on the windward side of the windward cooling structure 2000 can be effectively captured and guided to the flow guide cavity 3100 after completing the cooling of the gaseous working medium in the cooling cavity 2100. The flow guide cavity 3100 converges and rectifies the airflow, so that it can smoothly and efficiently enter the duct 310 through the flow guide opening 330. This design significantly reduces the disordered diffusion and energy loss of the airflow after passing through the windward cooling structure 2000, avoiding the negative impact of the airflow on the working efficiency of the propeller 200. By optimizing the import of the airflow, not only the thrust efficiency of the propeller 200 is improved, but also the airflow used for cooling can be fully utilized, thereby improving the heat dissipation performance of the entire thermal management device. The scheme changes the windward cooling structure 2000 from a simple heat dissipation component to an integrated airflow management assembly, realizing the synergistic optimization of heat dissipation and propulsion efficiency.

[0064] The present application further proposes that the flow guide plate group 3000 includes an outer plate body 3200 and an inner plate body 3300. The outer plate body 3200 is sealingly connected to the connecting pipe body 2200 and the outer wall of the adjacent air duct 300 on the circumferential side, so as to ensure the integrity of the flow guide cavity 3100 and the sealing of the airflow, preventing leakage of the airflow before entering the flow guide opening 330, thereby ensuring that the airflow can flow along the preset path. The inner plate body 3300 is arranged on the side of the outer plate body 3200 close to the windward cooling structure 2000, which functions to preliminarily guide and divide the airflow passing through the windward cooling structure 2000. The inner plate body 3300 is provided with a first flow guide surface 3310 and a second flow guide surface 3320 which are respectively inclined towards the adjacent flow guide openings 330. This inclined design enables the airflow to be actively guided and accelerated when passing through the inner plate body 3300, so that it can more smoothly and uniformly enter the corresponding flow guide openings 330 through the first flow guide surface 3310 and the second flow guide surface 3320. The first flow guide surface 3310 and the second flow guide surface 3320 can be optimally designed according to the positions of the flow guide openings 330 and the characteristics of the airflow, such as adjusting the inclination angle and curvature, so as to maximize the guiding efficiency and uniformity of the airflow.

[0065] In an embodiment, the present application further proposes that the middle region of the inner plate body 3300 is protrudingly arranged to form a structure with a V-shaped cross section, so that the two sides of the inner plate body 3300 respectively form the first flow guide surface 3310 and the second flow guide surface 3320 which are inclinedly arranged.

[0066] Specifically, the middle region of the inner plate body 3300 is protrudingly arranged to form a V-shaped structure in cross-section, which means that the inner plate body 3300 protrudes outward at its central part, and its cross-section presents a V shape. This V-shaped structure can be an acute V shape, an obtuse V shape, or a V shape with a circular arc transition. This protruding design aims to change the flow direction of the airflow, so that it can be more effectively guided. The V-shaped structure can split the oncoming airflow and guide it along the two slopes of the V shape. The V-shaped structure can be formed by one-piece molding, bending, welding, or riveting, etc. The specific angle and depth of the V-shaped structure can be optimized according to the airflow characteristics and flow guiding requirements to ensure that the airflow can be smoothly and efficiently guided to the flow guiding port 330.

[0067] At the same time, the two sides of the inner plate body 3300 are respectively formed into the first flow guiding surface 3310 and the second flow guiding surface 3320 arranged obliquely, which means that the two slopes of the V-shaped structure naturally form two inclined flow guiding surfaces, namely the first flow guiding surface 3310 and the second flow guiding surface 3320. These flow guiding surfaces are inclined relative to the initial direction of the airflow. These two inclined flow guiding surfaces are directly responsible for guiding the airflow from the leeward side of the windward cooling structure 2000 to the flow guiding port 330 of the adjacent duct 300. The design of the inclination angle is crucial for the smooth transition of the airflow and the reduction of energy loss. The inclination angles of the first flow guiding surface 3310 and the second flow guiding surface 3320 are usually determined according to the principles of fluid mechanics and actual airflow simulation results. They can be flat slopes or arc-shaped slopes with certain curvature to further optimize the flow characteristics of the airflow. For example, they can be designed to accelerate or decelerate the airflow on the flow guiding surface to adapt to the geometry of the subsequent flow guiding port 330 and the airflow requirements.

[0068] In an embodiment, the present application further proposes that the flow areas of the flow guiding ports 330 communicating with the same flow guiding cavity 3100 are equal, and the sum of the flow areas of the flow guiding ports 330 communicating with the same flow guiding cavity 3100 is greater than or equal to the flow area of the windward cooling structure 2000.

[0069] Specifically, the flow areas of the flow guiding ports 330 communicating with the same flow guiding cavity 3100 are equal, which means that among the multiple flow guiding ports 330 connected to the same flow guiding cavity 3100, the cross-sectional area of each flow guiding port 330 allowing airflow to pass through is the same. This can be achieved by precisely designing and manufacturing the geometry and size of the flow guiding ports 330, for example, all flow guiding ports 330 can be designed as the same circular, square or rectangular openings with consistent cross-sectional areas. This design helps to ensure that the airflow is evenly distributed among the flow guiding ports 330 before entering the duct 310, avoiding excessive resistance due to small area or excessive concentration of airflow due to large area in some flow guiding ports 330, thereby affecting the balance of the overall airflow.

[0070] Meanwhile, the sum of the flow areas of the flow guide ports 330 connected to the same flow guide cavity 3100 is greater than or equal to the flow area of the windward cooling structure 2000, which means that the sum of the effective flow areas of all the flow guide ports 330 connected to the same flow guide cavity 3100 is compared with the effective flow area allowed by the windward cooling structure 2000. By ensuring that the total flow area of the flow guide ports 330 is large enough, the pressure loss of the airflow passing through the flow guide cavity 3100 can be minimized, and the airflow flowing out of the windward cooling structure 2000 can smoothly pass through the flow guide cavity 3100 and enter the duct 310, without forming significant back pressure or hindering at the flow guide ports 330. If the sum of the flow areas of the flow guide ports 330 is less than the flow area of the windward cooling structure 2000, the flow guide ports 330 will become the bottleneck of the entire airflow path, limiting the amount of airflow passing through, thereby reducing the cooling efficiency. This can be achieved by optimizing the number, size and layout of the flow guide ports 330, for example, the number of flow guide ports 330 can be increased, or the size of a single flow guide port 330 can be increased to achieve the required total flow area.

[0071] In an embodiment, the branch cavity 2310 can be arranged to extend along the vertical direction, or the branch cavity 2310 can be arranged to extend along the vertical direction with an inclination, or the branch cavity 2310 can be arranged to extend along the circumferential direction of the wind tunnel 300. Specifically, when the branch cavity 2310 is arranged to extend along the vertical direction, the main axis thereof is parallel to the direction of gravity, so that after the gaseous working medium is condensed into liquid working medium, it can flow downward smoothly under the action of gravity, effectively returning to the end of the heat dissipation cavity 410 close to the power motor 100, thereby ensuring the continuity of the working medium circulation. At the same time, the extension in the vertical direction is also conducive to efficient heat exchange with the airflow in the vertical direction, enhancing the cooling effect. When the branch cavity 2310 is arranged to extend along the vertical direction with an inclination, the main axis thereof forms a non-zero angle with the vertical direction. By adjusting the inclination angle, the return path and speed of the working medium can be flexibly optimized according to the specific installation space of the aircraft, the flight attitude or the expected airflow direction, avoiding accumulation of the working medium in the branch cavity 2310, for example, the working medium can be designed to accelerate the return under the action of gravity along the inclined direction, while also adapting to the change of the gravity component under different flight attitudes. When the branch cavity 2310 is arranged to extend along the circumferential direction of the wind tunnel 300, the main axis thereof extends around the central axis of the wind tunnel 300. This layout can make full use of the space on the outer circumferential side of the wind tunnel 300, realizing a compact structure design. At the same time, the circumferentially extending branch cavities 2310 can be more evenly distributed around the wind tunnel 300, which is helpful to realize uniform cooling of the gaseous working medium, and can produce a specific interaction with the airflow formed by the propeller 200 in the duct 310, further optimizing the heat exchange efficiency.

[0072] By the technical solution, the specific extension direction of the branch cavity 2310 is determined, thereby effectively solving the problems of working medium retention and poor backflow, and significantly improving the cooling efficiency and reliability of the thermal management device. These different extension modes enable the thermal management device to select the most suitable cooling cavity 2100 layout according to specific application scenarios and design requirements, ensuring that the gaseous working medium can be efficiently condensed and backflowed under various working conditions, maintaining the optimal working temperature of the power motor 100, prolonging the service life of the power motor 100, and improving the overall performance of the aircraft.

[0073] In an embodiment, as shown in Figure 1 and Figures 3-5 shown, the present application further proposes that the above-mentioned windward cooling structure 2000 further comprises fins 450, and a plurality of cooling pipe bodies 2300 are respectively arranged in the fins 450 and are in heat-conducting contact with the fins 450. The fins 450 can be made of materials with good heat-conducting properties, such as aluminum, copper and their alloys, to ensure efficient heat conduction. The shape of the fins 450 can be designed in various forms according to actual needs, such as plate-shaped, corrugated, needle-shaped, grid-shaped, etc., to adapt to different space limitations and airflow conditions. The fins 450 are usually tightly combined with the cooling pipe bodies 2300 by welding, brazing, pipe expansion or mechanical pressing, etc., to ensure good heat-conducting contact between them, thereby minimizing the thermal resistance in the heat transfer process. Moreover, the fins 450 can be arranged horizontally or obliquely.

[0074] In an embodiment, the present application further proposes that 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 lift surface, and along the direction from the front side of the aircraft to the rear side of the aircraft, the height of the lift surface increases first and then decreases, and the lower end surface of the support pipe body 430 is a plane. 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 drop-shaped.

[0075] In an embodiment, as shown in Figure 7 , the present application further proposes that the evaporation cavity 421 comprises a backflow channel 422 and a collection cavity 423, a plurality of condensation pipe cavities 431 are distributed and communicated to the outer peripheral side of the backflow channel 422, the collection cavity 423 is arranged at one end of the backflow channel 422 close to the power motor 100 and is communicated to the backflow channel 422, the collection cavity 423 is in heat-conducting contact with the heat-generating end of the power motor 100. One end of the backflow channel 422 communicated to the collection cavity 423 is provided with an expanded cavity 426, and along the direction from the backflow channel 422 to the collection cavity 423, the flow area of the expanded cavity 426 increases.

[0076] By subdividing the evaporation cavity 421 into the reflux channel 422 and the collection cavity 423, and optimizing the connection mode of the condenser tube cavity 431 and the reflux channel 422, the application can effectively organize the reflux path of the liquid working medium and the generation and flow of the gaseous working medium. Specifically, the direct heat conduction contact of the collection cavity 423 with the heat generation end of the power motor 100 ensures that heat can be efficiently transferred to the liquid working medium, promoting its rapid gasification. The plurality of condenser tube cavities 431 are uniformly connected to the outer peripheral side of the reflux channel 422, ensuring stable and uniform reflux of the working medium. Further, the reflux channel 422 is connected to the flared cavity 426 provided at one end of the collection cavity 423, and the flow area thereof increases in the direction of the collection cavity 423, significantly reducing the resistance of the liquid working medium reflux, and optimizing the fluid dynamics of the ascending gaseous working medium, effectively separating the gas-liquid two-phase, avoiding the liquid working medium being entrained by the ascending gas flow, thereby preventing the occurrence of local dryout phenomenon, and improving the efficiency and stability of the phase change heat transfer. This refined evaporation cavity 421 structure design significantly improves the heat dissipation performance of the thermal management device for the power motor 100, ensuring the reliability of the power motor 100 under long-time operation.

[0077] In an embodiment, the application further proposes a structure for optimizing the gas-liquid two-phase flow, specifically, the head fairing 500 is provided at one end of the reflux channel 422 away from the collection cavity 423, and the cross-sectional area of the head fairing 500 decreases along the direction from the collection cavity 423 to the reflux channel 422, so as to reduce the wind resistance. Similarly, the tail fairing 600 is provided at one end of the power motor 100 away from the collection cavity 423, and the cross-sectional area of the tail fairing 600 decreases along the direction from the reflux channel 422 to the collection cavity 423, so as to prevent turbulence at the tail.

[0078] In an embodiment, the application further proposes that the support heat dissipation structure 400 further comprises a pumping assembly 460, a delivery 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 separates the collection cavity 423 into a first cavity 424 close to the reflux channel 422 and a second cavity 425 close to the power motor 100, and the upper end of the liquid blocking plate 480 and the inner wall of the collection cavity 423 are spaced apart to form a vapor passage 490. The liquid working medium refluxed by the condenser tube cavity 431 can enter the first cavity 424 through the lower side area of the reflux channel 422, one end of the delivery pipe 470 is immersed in the liquid working medium of the first cavity 424, the other end crosses the vapor passage 490 and extends into the second cavity 425, the pumping assembly 460 can transport the liquid working medium from the first cavity 424 to the second cavity 425 through the delivery pipe 470, and the liquid working medium in the second cavity 425 can be heated and gasified into gaseous working medium and enter the condenser tube cavity 431 through the vapor passage 490 and the upper side area of the reflux channel 422.

[0079] The pumping assembly 460 is used to actively transport the liquid working medium to overcome the gravity, surface tension or flow resistance, to ensure that the liquid working medium can be efficiently and stably transported from the collection area to the evaporation area. It can take various forms, such as a micro centrifugal pump, a magnetic pump, a piezoelectric pump or a peristaltic pump, etc. The delivery pipe 470 is a channel for guiding the liquid working medium from the first cavity 424 to the second cavity 425, which is usually an elongated tubular structure. The liquid baffle 480 is arranged in the collection cavity 423, which mainly functions to separate the collection cavity 423 into two independent areas, i.e. the first cavity 424 and the second cavity 425, and at the same time forms a vapor passage 490. The lower end of the liquid baffle 480 is in sealing connection with the inner wall of the collection cavity 423, ensuring that the liquid working medium can only be actively transported between the first cavity 424 and the second cavity 425 through the delivery pipe 470. The upper end of the liquid baffle 480 leaves a gap with the inner wall of the collection cavity 423, forming a vapor passage 490, which allows the gaseous working medium generated in the second cavity 425 to flow upward into the upper area of the reflux passage 422, and then into the condensing pipe cavity 431.

[0080] The first cavity 424 is the part of the collection cavity 423 close to the reflux passage 422 after being separated by the liquid baffle 480, mainly used for receiving and temporarily storing the liquid working medium refluxed from the condensing pipe cavity 431. The liquid working medium enters this cavity through the lower area of the reflux passage 422. The second cavity 425 is the part of the collection cavity 423 close to the heat-emitting surface of the power motor 100 after being separated by the liquid baffle 480, which is the main area for the liquid working medium to actively transport and gasify after being heated. The delivery pipe 470 directly transports the liquid working medium to this cavity, allowing it to make full contact with the heat-emitting surface of the power motor 100 for efficient heat absorption and gasification. The vapor passage 490 is the gap between the upper end of the liquid baffle 480 and the inner wall of the collection cavity 423, which provides a path for the gaseous working medium generated in the second cavity 425 to flow upward, allowing it to smoothly enter the upper area of the reflux passage 422 and further enter the condensing pipe cavity 431 for condensation.

[0081] Specifically, the liquid working medium flowing back in the condenser tube cavity 431 flows along the lower side area of the backflow channel 422 under the action of gravity or surface tension, and finally collects in the first cavity 424. The liquid inlet end of the delivery pipe 470 is deep into the liquid working medium in the first cavity 424, ensuring that the pumping assembly 460 can continuously extract liquid. The liquid outlet end crosses the vapor channel 490, directly sending the liquid working medium into the second cavity 425, avoiding unnecessary flow or interference with the gaseous working medium in the vapor channel 490. After the pumping assembly 460 is started, a pressure difference is generated, driving the liquid working medium to be passively collected from the first cavity 424 to the second cavity 425 by the delivery pipe 470. In the second cavity 425, the liquid working medium vaporizes after absorbing the heat generated by the power motor 100. The generated gaseous working medium flows upward through the vapor channel 490 above the liquid blocking plate 480, enters the upper side area of the backflow channel 422, and is then guided to the condenser tube cavity 431 for condensation.

[0082] Through the above technical solution, the pumping assembly 460, the delivery pipe 470, and the liquid blocking plate 480 are introduced into the support heat dissipation structure 400, and the collection cavity 423 is divided, realizing the active circulation of the liquid working medium. Specifically, the liquid working medium flowing back in the condenser tube cavity 431 first collects in the first cavity 424, and the pumping assembly 460 actively delivers the liquid working medium from the first cavity 424 to the second cavity 425 close to the power motor 100 through the delivery pipe 470. This active delivery mechanism ensures that the power motor 100 has sufficient supply of liquid working medium in the heating area, effectively avoiding the problem of insufficient or uneven backflow of liquid working medium under complex working conditions such as aircraft attitude change, high heat load, or unfavorable gravity direction, thereby preventing local overheating of the power motor 100. At the same time, the liquid blocking plate 480 divides the collection cavity 423 into a liquid working medium collection area (the first cavity 424) and an evaporation area (the second cavity 425), and forms an independent vapor channel 490, so that the delivery path of the liquid working medium and the discharge path of the gaseous working medium are clearly separated, optimizing the efficiency of two-phase flow and reducing the flow resistance caused by gas-liquid mixing. This significantly improves the stability and heat dissipation performance of the thermal management system, ensuring that the power motor 100 can maintain an optimal working temperature under various operating conditions, thereby prolonging the service life of the power motor 100 and improving the overall reliability of the aircraft.

[0083] Specifically, in an embodiment, the vertical height of the vapor 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 vapor channel 490 and the vertical height of the stator winding of the power motor 100 is between 3mm-5mm.

[0084] By the above technical solution, the vertical height of the vapor passage 490 is accurately controlled to be greater than the vertical height of the stator winding of the power motor 100, and the height difference is limited to 3-5 mm, thereby providing an optimized and unobstructed flow path for the gaseous working medium generated from the stator winding of the power motor 100. This significantly reduces the flow resistance of the gaseous working medium in the evaporation area, effectively avoids the local retention or "gas lock" phenomenon of the gaseous working medium, thereby ensuring that the liquid working medium can continuously and efficiently absorb the heat generated by the power motor 100 and vaporize. The gaseous working medium can quickly leave the evaporation area and enter the condensation area, maintaining a stable two-phase heat transfer cycle, thereby effectively controlling the operating temperature of the power motor 100, preventing overheating, and ensuring the stability and reliability of the thermal management device under various working conditions.

[0085] In an embodiment, the power motor 100, the second cavity 425, the first cavity 424, and the return passage 422 are sequentially arranged along the axial direction of the air duct 300. Sequentially arranging these components along the axial direction of the air duct 300 means that these components are linearly arranged along the central axis of the air duct 300 in space. For example, they can be arranged in the order of the power motor 100, the second cavity 425, the first cavity 424, and the return passage 422 from one end of the air duct 300 to the other end, or the axial order can be adjusted according to actual needs. This axial arrangement helps to form a compact structure, reduces the radial size of the thermal management device, and optimizes the path of the working medium during evaporation, flow, and return, thereby improving heat exchange efficiency and system integration.

[0086] In an embodiment, the application further proposes that the flow area of the vapor passage 490 is greater than or equal to the flow area of the return passage 422, and the flow area of the return passage 422 is greater than or equal to the sum of the flow areas of the plurality of condensation tube cavities 431.

[0087] By the above technical solution, the flow areas of the vapor passage 490, the return passage 422, and the condensation tube cavities 431 are reasonably matched, ensuring that the flow resistance of the gaseous working medium in the vapor passage 490 and the return passage 422 is minimized, avoiding accumulation of the gaseous working medium and excessive local pressure drop. At the same time, the flow area of the return passage 422 is large enough to accommodate the return of the liquid working medium from the plurality of condensation tube cavities 431, ensuring smooth return of the liquid working medium and preventing the liquid working medium from being retained in the condensation tube cavities 431 or the return passage 422, thereby maintaining the stability of the working medium circulation. This design optimizes the transmission efficiency of the gas-liquid two-phase flow, so that the heat generated by the power motor 100 can be more effectively removed, improving the overall heat dissipation performance and reliability of the thermal management device, and ensuring the thermal stability of the aircraft under long-time flight or high-load operation.

[0088] In an embodiment, the application further proposes a specific implementation of the pumping assembly 460, which is a magnetic coupling pump. The magnetic coupling pump comprises a magnetic driver and a magnetic impeller assembly. The magnetic driver is directly mounted to the output end of the power motor 100 or mounted to the output end of the power motor 100 through a transmission assembly. The power motor 100 can drive the magnetic driver to rotate. The magnetic impeller assembly is installed inside the delivery pipe 470. When the power motor 100 works, the rotating magnetic field of the magnetic driver can drive the magnetic impeller assembly to rotate synchronously. The centrifugal force generated by the magnetic impeller assembly can pump the liquid working medium in the first cavity 424 into the delivery pipe 470 and delivered to the second cavity 425.

[0089] The magnetic coupling pump is a non-contact pump that transmits torque by magnetic force. Its core advantage is that it can realize the delivery of fluid without mechanical seal, thereby effectively avoiding the leakage problem that may exist in traditional mechanical seal pumps. The magnetic driver is responsible for generating a rotating magnetic field, which is usually composed of permanent magnets or electromagnetic coils, and is directly connected with the output end of the power motor 100 or connected through a transmission assembly. When the power motor 100 works, its rotating motion is transmitted to the magnetic driver, so that it rotates synchronously, thereby generating a rotating magnetic field that drives the magnetic impeller assembly. The magnetic impeller assembly is installed inside the delivery pipe 470, and its inside or outside is provided with a magnetic material matched with the magnetic driver. Under the action of the rotating magnetic field generated by the magnetic driver, the magnetic impeller assembly is driven to rotate synchronously, and the centrifugal force generated by its blades sucks the liquid working medium in the first cavity 424 and delivers it along the delivery pipe 470 to the second cavity 425. This non-contact driving mode ensures the complete sealing of the working medium, and is particularly suitable for working medium circulation systems that are sensitive to leakage.

[0090] Specifically, when the magnetic coupling pump is used as the pumping assembly 460, due to its mechanical seal-free characteristic, it can fundamentally eliminate the risk of leakage of the liquid working medium, which is crucial for a thermal management system containing volatile or corrosive working medium, and significantly improves the safety and reliability of the system. At the same time, the magnetic coupling pump can be directly or through a transmission assembly connected with the output end of the power motor 100, and use the rotating energy of the power motor 100 itself to drive the pumping, realizing the integration of the power source, simplifying the system structure, and reducing the overall weight and volume, which has significant advantages for aircraft.

[0091] In another embodiment, the pumping assembly 460 comprises a controller, a liquid pump and a liquid level sensor, which 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 detects that the liquid level of the liquid working medium in the first cavity 424 is higher than the first preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first cavity 424 to the second cavity 425 through the delivery pipe 470. Alternatively, when the liquid level sensor is arranged in the second cavity 425 and detects that the liquid level of the liquid working medium in the second cavity 425 is lower than the second preset liquid level, the controller can control the liquid pump to start working and transport the liquid working medium from the first cavity 424 to the second cavity 425 through the delivery pipe 470.

[0092] The controller, the liquid pump and the liquid level sensor are a liquid working medium delivery scheme based on feedback control, which aims to accurately adjust the supply of liquid working medium according to actual needs. The liquid level sensor is used to monitor the liquid level of the liquid working medium in the first cavity 424 or the second cavity 425 in real time. It can be of various types such as float type, capacitive type, ultrasonic type, etc., and its function is to provide liquid level information to the controller. The controller is the core of the entire feedback system, which receives the liquid level signal provided by the liquid level sensor and determines whether the liquid pump needs to be started or stopped according to the preset control logic. For example, when the liquid level in the first cavity 424 is higher than the preset value (indicating that the backflow of the liquid working medium is sufficient) or the liquid level in the second cavity 425 is lower than the preset value (indicating that the liquid working medium in the heat generating area is insufficient), the controller will issue an instruction to start the liquid pump. The liquid pump is an execution component that transports the liquid working medium from the first cavity 424 to the second cavity 425 through the delivery pipe 470 according to the instruction of the controller. The liquid pump can be a micro centrifugal pump, a gear pump or a peristaltic pump, etc., and its selection needs to consider factors such as flow rate, head, volume and power consumption. This control method can realize the on-demand supply of liquid working medium, avoid unnecessary energy consumption, and improve the response speed and stability of the system.

[0093] Through the above technical solutions, the present application provides two efficient and reliable implementation ways for the pumping assembly 460 of the liquid working medium in the thermal management device, effectively solving the technical problem of how to ensure the stable and accurate circulation of the liquid working medium and avoid leakage in the compact and dynamic aircraft environment.

[0094] In an embodiment, the present application provides a thermal management device, wherein the support heat dissipation structure 400 is arranged on the front side of the rotor assembly 1000, and the propeller 200 is arranged on the rear side of the rotor assembly 1000.

[0095] Specifically, the support heat dissipation structure 400 is a component for supporting the power motor 100 and dissipating heat, which is internally provided with a heat dissipation cavity 410 for heat transfer through phase change of the liquid working medium. It is arranged on the front side of the aircraft, which means that in the forward direction of the aircraft, the support heat dissipation structure 400 first contacts the oncoming external airflow. This is conducive to the external airflow directly and effectively passing through the head-on cooling structure 2000 and cooling the gaseous working medium in the heat dissipation cavity 410 in the flight state. The propeller 200 is a component for generating thrust, which drives the airflow by rotating to enable the aircraft to obtain lift or thrust. The propeller 200 is arranged on the rear side of the rotor assembly 1000, which means that it is located behind the support heat dissipation structure 400. When the propeller 200 rotates, it forms an airflow that flows axially along the wind tunnel 300 in the duct 310. This layout helps to form a serial cooling airflow path, that is, the external airflow first cools the support heat dissipation structure 400, and then the airflow generated by the propeller 200 further cools or discharges heat. This front-rear layout not only makes full use of the external airflow of the rotor assembly 1000 and the airflow generated by the propeller 200 when the aircraft is flying, realizes more stable and efficient thermal management of the power motor 100, but also avoids the adverse effects of the support heat dissipation structure 400 on the working efficiency of the propeller 200, ensuring the overall aerodynamic performance and propulsion efficiency of the aircraft.

[0096] Specifically, in an embodiment, the distance B between the support heat dissipation structure 400 and the propeller 200 satisfies 1mm≤B≤20mm, preferably 2mm≤B≤10mm.

[0097] In an embodiment, the inlet of the duct 310 and the outlet of the duct 310 are both non-circular in shape, and the duct 310 is provided with a section of the propeller 200 which is circular in shape.

[0098] Wherein, the inlet of the duct 310 refers to the entrance of the airflow into the duct 310, and the outlet refers to the exit of the airflow from the duct 310. Non-circular shape means that these sections are not standard circular, and can be elliptical, rectangular, irregular or other irregular shapes. The inlet and outlet can be designed according to the specific aerodynamic layout of the aircraft, the installation space limitation and the desired airflow characteristics. For example, it can be designed as a flat ellipse to reduce the windward area, or as an irregular shape that blends with the wing or fuselage to achieve a smoother aerodynamic shape. This non-circular shape can be manufactured by mold forming, 3D printing or multi-component splicing, etc.

[0099] The section of the propeller 200 refers to the cross-section of the duct 310 within the swept area of the propeller 200 blades. The circular shape means that the inner wall of the duct 310 in the region is a standard circle. The propeller 200 is usually designed to be most efficient when working in a circular cross-section, because the circular cross-section can provide uniform tip clearance, reduce tip vortex loss, and ensure uniform acceleration of airflow in the propeller 200 region. Therefore, inside the duct 310, the part corresponding to the swept area of the propeller 200 blades can be precisely machined into a circular shape to match the diameter of the propeller 200, ensuring optimal aerodynamic performance. This can be achieved by one-piece molding or embedding a circular bushing inside the non-circular duct 310 body.

[0100] In an embodiment, the present application proposes an optimization scheme, i.e. when the structural wall thickness of the thermal management device is greater than or equal to 3mm, the side wall of the thermal management device is a hollow structure or a porous structure.

[0101] By the above technical scheme, the side wall of the thermal management device with a wall thickness greater than or equal to 3mm is designed as a hollow structure or a porous structure, effectively solving the problems of weight increase and heat transfer efficiency reduction caused by solid thick wall. The hollow structure or the porous structure can significantly reduce the overall weight of the device, thereby reducing the energy consumption of the aircraft, prolonging the endurance time, and improving the flight performance. At the same time, the cavities or pores inside these structures can act as additional thermal insulation layers, reducing unnecessary heat loss, or under certain designs, enhancing heat transfer through the flow of internal fluids, optimizing thermal management efficiency. For example, the hollow structure can form internal flow channels to guide airflow or liquid working medium for auxiliary cooling. The porous structure can provide a larger surface area to promote heat exchange. Therefore, the scheme realizes lightweight and thermal performance optimization under the premise of ensuring structural strength.

[0102] In an embodiment, the present application proposes an aircraft. The aircraft refers to a vehicle or device capable of flying in the atmosphere, which overcomes gravity by generating lift and uses thrust to achieve forward progress. The aircraft in the present application can be a drone, a multi-rotor aircraft, a fixed-wing aircraft or any other aircraft that requires an efficient thermal management system. Integrating the above thermal management device into the aircraft means that the aircraft will carry at least one thermal management unit containing a power motor 100, a propeller 200, a wind tunnel 300 and a support heat dissipation structure 400 and a windward cooling structure 2000. This integrated manner makes the overall design of the aircraft need to consider the size, weight, installation position of the thermal management device and its required air inlet and exhaust path to ensure that the thermal management device can work effectively and cooperate with other systems of the aircraft. For example, in a multi-rotor drone, the thermal management device can be installed as part of each rotor assembly 1000 at the end of the arm. In a fixed-wing aircraft, it can be integrated into the ducted 310 propulsion system inside the wing or fuselage.

[0103] By integrating the above thermal management device into the aircraft, the aircraft can obtain efficient and stable power motor 100 heat dissipation capability. This ensures that the power motor 100 can maintain within the optimal working temperature range under various flight conditions, including high load, long time operation or different environmental temperature, thereby significantly improving the power output efficiency and continuous flight capability of the aircraft. At the same time, effective thermal management can greatly prolong the service life of the power motor 100, reduce the failure rate, and thus improve the overall reliability and safety of the aircraft. In addition, the integrated design of the thermal management device helps to optimize the aerodynamic layout of the aircraft, reduce unnecessary resistance, and may bring more compact and lightweight advantages to the overall structural design of the aircraft, thereby improving the overall performance of the aircraft.

[0104] The technical features of the above embodiments can be combined in any way. To make the description concise, not all possible combinations of the technical features in the above embodiments are described, but as long as the combinations of the technical features do not exist contradictory, they should be considered as the scope of the present application.

[0105] The above embodiments only express several implementation manners of the present application, and the description is more specific and detailed, but it should not be understood as a limitation on the scope of the application. It should be pointed out that for ordinary skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are within the scope of the present application. Therefore, the application protection scope of the present application should be subject to the appended claims.

[0106] In the description of the application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the purpose of facilitating the description of the application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the application.

[0107] In this application, unless otherwise clearly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium; it can be the internal communication of two elements or the interaction relationship of two elements, unless otherwise clearly specified and limited. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0108] 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 terms used in the specification of the application herein are only for the purpose of describing the specific embodiments and are not intended to limit the application. The term "and / or" used herein includes any and all combinations of one or more related listed items.

Claims

1. A thermal management device, characterized in that, It includes at least two rotor assemblies (1000) and at least one windward cooling structure (2000), each of the windward cooling structures (2000) being connected to two adjacent rotor assemblies (1000), each rotor assembly (1000) including: Power motor (100); A propeller (200) is connected to the output end of the power motor (100), which can drive the propeller (200) to rotate. A duct (300) is provided with a duct (310) extending along its own axial direction. The duct (300) is fitted onto the outer periphery of the power motor (100) and the propeller (200) through the duct (310); and, A heat dissipation support structure (400) is provided, through which the power motor (100) is installed on the inner wall of the duct (310), and the heat dissipation support structure (400) is provided with a heat dissipation cavity (410). The windward cooling structure (2000) is provided with a cooling chamber (2100). One end of the heat dissipation chamber (410) is in thermal contact with the power motor (100), and the other end extends towards the direction close to the air duct (300) and connects to the cooling chamber (2100). The heat dissipation chamber (410) contains a liquid working fluid, which can absorb heat and vaporize, and flow along the extension direction of the heat dissipation chamber (410) to the cooling chamber (2100). The propeller (200) can be driven by the duct (310). An airflow is formed within the air duct (300) to flow along the axial direction, causing the gaseous working fluid in the heat dissipation cavity (410) to release heat and liquefy. When the aircraft is in flight, the external airflow can pass through the outer wall of the cooling cavity (2100), causing the gaseous working fluid in the cooling cavity (2100) to release heat and liquefy. Both the gaseous working fluid in the heat dissipation cavity (410) and the cooling cavity (2100) can condense and flow back to the end of the heat dissipation cavity (410) near the power motor (100).

2. The thermal management device according to claim 1, characterized in that, The axes of the plurality of rotor assemblies (1000) are arranged in parallel, and the plurality of rotor assemblies (1000) are arranged side by side along a direction perpendicular to their own axes. The two ends of the windward cooling structure (2000) are respectively fixedly connected to the adjacent rotor assemblies (1000).

3. The thermal management device according to claim 1, characterized in 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 located in the evaporation section (420) and contains a liquid working fluid. At least a portion of the support tube (430) is provided with the condensation cavity (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) and connects to the cooling cavity (2100).

4. The thermal management device according to claim 3, characterized in that, The height of the end of the condenser tube (431) away from the evaporator (421) is greater than or equal to the maximum height of the evaporator (421); The supporting tube (430) having the condenser cavity (431) is defined as the condenser tube, which extends radially toward the upper end of the air duct (300).

5. The thermal management device according to claim 4, characterized in that, The air duct (300) is provided with a first balancing chamber (320), which extends along the circumference of the air duct (300). The condenser tube cavities (431) of the plurality of condenser tubes are respectively connected to the first balancing chamber (320) at the ends away from the evaporation chamber (421). The windward cooling structure (2000) includes a connecting pipe (2200) and a cooling pipe (2300). The two ends of the connecting pipe (2200) are respectively connected to the outer wall of the adjacent air duct (300). One end of the cooling pipe (2300) is connected to the outer wall of the air duct (300), and the other end is connected to the connecting pipe (2200) or the adjacent cooling pipe (2300). The cooling chamber (2100) includes a second balancing chamber (2210) and a branch chamber (2310). The second balancing chamber (2210) is located in the connecting pipe (2200), and the branch chamber (2310) is located in the corresponding cooling pipe (2300). One end of the branch chamber (2310) is connected to the first balancing chamber (320), and the other end is connected to the second balancing chamber (2210) or the adjacent branch chamber (2310).

6. The thermal management device according to claim 5, characterized in that, The two first balancing chambers (320) of the adjacent air duct (300) and the second balancing chamber (2210) of the connecting pipe (2200) are connected in sequence to form an annular channel structure surrounding the outer periphery of the branch chamber (2310).

7. The thermal management device according to claim 5, characterized in that, It also includes a guide vane assembly (3000), which is disposed on the leeward side of the windward cooling structure (2000). The guide vane assembly (3000), the windward cooling structure (2000), and the outer wall of the adjacent air duct (300) form a guide cavity (3100). Furthermore, the side walls of the adjacent air duct (300) are respectively provided with guide ports (330) that communicate with the guide cavity (3100). When the propeller (200) rotates, the airflow on the windward side of the windward cooling structure (2000) can sequentially pass through the windward cooling structure (2000), the guide cavity (3100), and the guide port (330) into the duct (310).

8. The thermal management device according to claim 7, characterized in that, The guide plate assembly (3000) includes an outer plate (3200) and an inner plate (3300). The outer plate (3200) is sealed to the periphery of the connecting pipe (2200) and the outer wall of the adjacent air duct (300). The inner plate (3300) is disposed on the side of the outer plate (3200) near the windward cooling structure (2000). The inner plate (3300) is provided with a first guide surface (3310) and a second guide surface (3320) that are inclined toward the adjacent guide port (330) so that the airflow can enter the adjacent guide port (330) through the first guide surface (3310) and the second guide surface (3320) respectively.

9. The thermal management device according to claim 7, characterized in that, The flow areas of the flow ports (330) connected to the same flow guide cavity (3100) are equal, and the sum of the flow areas of the flow ports (330) connected to the same flow guide cavity (3100) is greater than or equal to the flow area of ​​the windward cooling structure (2000).

10. The thermal management device according to claim 3, characterized in 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. The return channel (422) is connected to the collection cavity (423) at one end, and the expansion cavity (426) has an increasing flow area along the direction from the return channel (422) to the collection cavity (423).

11. The thermal management device according to claim 10, characterized in that, The supporting heat dissipation structure (400) further 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) and divides the collecting cavity (423) into a first cavity (424) near the return channel (422) and a second cavity (425) near the power motor (100). The upper end of the baffle plate (480) and the inner wall of the collecting cavity (423) are spaced apart to form a vapor channel (490). 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 deliver the liquid working fluid from the first cavity (424) to the second cavity (425) through the delivery pipe (470). The liquid working fluid in the second cavity (425) can absorb heat and vaporize into a gaseous working fluid and enter the condenser cavity (431) through the upper region of the vapor channel (490) and the return channel (422).

12. The thermal management device according to claim 11, characterized in that, The pumping assembly (460) is a magnetic coupling pump, which includes a magnetic actuator and a magnetic impeller assembly. The magnetic actuator is directly installed at the output end of the power motor (100) or installed at the output end of the power motor (100) through a transmission assembly. The power motor (100) can drive the magnetic actuator to rotate. The magnetic impeller assembly is installed inside the delivery pipe (470). When the power motor (100) 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 medium in the first chamber (424) into the delivery pipe (470) and deliver it to the second chamber (425). Alternatively, the pumping assembly (460) includes a controller, a liquid pump, and a liquid level sensor, wherein the liquid level sensor is disposed in the first cavity (424) or the second cavity (425); when the liquid level sensor is disposed in the first cavity (424) and measures that the liquid level of the 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 transport the liquid working medium from the first cavity (424) to the second cavity (425) through the delivery pipe (470); or, when the liquid level sensor is disposed in the second cavity (425) and measures that the liquid level of the 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 transport the liquid working medium from the first cavity (424) to the second cavity (425) through the delivery pipe (470).

13. The thermal management device according to claim 1, characterized in that, The supporting heat dissipation structure (400) is disposed on the front side of the rotor assembly (1000), and the propeller (200) is disposed on the rear side of the rotor assembly (1000).

14. An aircraft, characterized in that, Includes the thermal management device as described in any one of claims 1-13.

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