Thermal management system and thermal management method for liquid metal of rudder shaft of aircraft

Abstract

The invention provides a liquid metal thermal management system and thermal management method for an aircraft rudder shaft. The system comprises a first subsystem and a second subsystem. The first subsystem comprises an aircraft rudder shaft, a heat exchanger and a driving pump which are connected in sequence; a first heat dissipation working medium of the first subsystem is liquid metal; the second subsystem comprises a pressure container and a heat exchanger, and a second heat dissipation working medium in the second subsystem is a working medium which is gas at normal temperature and normal pressure; the heat exchanger is used for heat exchange between the first heat dissipation working medium and the second heat dissipation working medium. According to the liquid metal thermal management system and thermal management method for the aircraft rudder shaft, cooling of the aircraft rudder shaft is achieved through heat exchange of the first heat dissipation working medium and the second heat dissipation working medium, and due to the fact that the first heat dissipation working medium is the liquid metal, on one hand, the boiling point of the liquid metal is usually larger than 1000 DEG C, and on the other hand, the heat dissipation efficiency is greatly improved; the problems of heat transfer deterioration, pipeline sealing reliability reduction and the like caused by working medium gasification in the water cooling technology are solved, and the heat extraction efficiency of the aircraft rudder shaft is further improved.

Description

Technical Field

[0001] The present invention relates to the field of thermal management technology, and in particular to a liquid metal thermal management system and a thermal management method for an aircraft rudder shaft. Background Art

[0002] When a high-speed aircraft enters or exits the atmosphere or continues to fly in space, the air in front of it is strongly compressed, and a violent viscous friction effect occurs between the surface of the aircraft and the air molecules. A large amount of molecular kinetic energy is converted into heat energy, causing the surface temperature of the aircraft to rise rapidly. This phenomenon is called aerodynamic heating. When the aircraft speed is low, the surface heat is easily dissipated. When the speed exceeds Mach 2.5, the large amount of aerodynamic heat generated cannot be dissipated in time, which will cause the surface temperature of the aircraft to rise sharply, resulting in reduced strength of the fuselage material, deformation of the outer shell, and even loss of flight control. This is called thermal barrier.

[0003] Among the thermal protection technologies for various parts of aircraft, there are relatively few protective measures for the rudder shaft of the air rudder. The air rudder consists of a rudder shaft and a rudder surface. The rudder surface is located outside the aircraft, and the rudder shaft is a fixed shaft connecting the rudder surface and the main body of the aircraft. Most of it is located inside the aircraft, but there is a section of the rudder shaft connected to the rudder surface that is directly exposed to the outside air. In order to ensure the reliability of the movement and control of the rudder surface, the surface of this section of the rudder shaft cannot be covered with insulation materials, which puts high requirements on the thermal protection of the rudder shaft. The use of fluid active cooling technology is expected to significantly reduce the surface temperature of the rudder shaft, and currently it is mainly based on water-cooled active cooling technology.

[0004] However, under the action of aerodynamic heat, the heat flux density on the surface of the rudder shaft section exposed to the outside of the aircraft can exceed 1MW / m 2 , the surface temperature reaches 700℃. The active cooling technology based on water cooling has problems such as deterioration of heat transfer due to gasification of working fluid and reduced reliability of pipeline sealing. Summary of the invention

[0005] The present invention provides a liquid metal thermal management system and a thermal management method for an aircraft rudder shaft, so as to solve the defects in the prior art that the thermal protection measures for the aircraft rudder shaft are simple and difficult to cope with the reduced strength and reliability of the rudder shaft caused by high aerodynamic heat, and realize efficient thermal protection of the aircraft rudder shaft.

[0006] The present invention provides a liquid metal thermal management system for an aircraft rudder shaft, comprising a first subsystem and a second subsystem; The first subsystem is a heat extraction circuit, comprising an aircraft rudder shaft, a heat exchanger and a driving pump connected in sequence; the driving pump is used to drive a first heat dissipation medium; and the first heat dissipation medium of the first subsystem is liquid metal; The second subsystem comprises a pressure vessel and the heat exchanger, wherein the pressure vessel is connected to the upstream of the heat exchanger; and the second heat dissipation medium in the second subsystem is a gaseous medium at normal temperature and pressure; and the pressure vessel is used to store the second heat dissipation medium; The heat exchanger is used for exchanging heat between the first heat dissipation medium and the second heat dissipation medium.

[0007] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the first subsystem further includes a controller, a flow meter and a temperature sensor network; the flow meter is arranged between the heat exchanger and the drive pump, and the flow meter is used to measure the flow rate of the first heat dissipation medium in real time; the input end of the temperature sensor network is connected to the aircraft rudder shaft, and the temperature sensor network is used to collect temperature data of various parts of the aircraft rudder shaft; The second subsystem further includes a flow regulator and the controller, wherein the flow regulator is used to adjust the flow of the second heat dissipation medium; The controller is electrically connected to the flow meter, the drive pump, the temperature sensor network and the flow regulator, and the controller is used to adjust the flow of the first heat dissipation fluid and the flow of the second heat dissipation fluid according to the temperature data and the flow of the first heat dissipation fluid.

[0008] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the heat exchanger is a shell-and-tube heat exchanger, which is provided with an inner tube and an outer ring, the inner tube accommodates the first heat dissipation medium, and the outer ring accommodates the second heat dissipation medium; and the outer ring is connected to the external environment.

[0009] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the first heat dissipation medium includes gallium-based liquid metal or gallium-based alloy liquid metal, and the second heat dissipation medium includes one of carbon dioxide, nitrogen, ammonia and methane.

[0010] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the flow meter includes an electromagnetic flow meter or an ultrasonic flow meter.

[0011] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the drive pump includes a DC conduction electromagnetic pump, an AC electromagnetic pump, a diaphragm pump or a piezoelectric pump.

[0012] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the temperature sensor network includes a wired sensor network and a wireless sensor network.

[0013] According to a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention, the pressure vessel comprises a storage pressure vessel or a reaction pressure vessel.

[0014] The present invention also provides a liquid metal thermal management method for an aircraft rudder shaft, using the liquid metal thermal management system for the aircraft rudder shaft as described above, comprising: A first heat dissipation medium flows in the first subsystem, the first heat dissipation medium is used to extract heat from the aircraft rudder shaft, and the first heat dissipation medium in the heat extraction circuit is liquid metal; A second heat dissipation medium flows in the second subsystem, and the second heat dissipation medium is a gaseous medium at normal temperature and pressure; The first heat dissipation medium and the second heat dissipation medium exchange heat through a heat exchanger.

[0015] According to the liquid metal thermal management method for an aircraft rudder shaft provided by the present invention, the first subsystem and the second subsystem exchange heat through a heat exchanger, comprising: Get the surface temperature of the aircraft's rudder shaft; Real-time monitoring of the flow rate of the first heat dissipation medium; Based on the surface temperature and the flow rate of the first heat dissipation fluid, the flow rates of the first heat dissipation fluid and the second heat dissipation fluid are adjusted.

[0016] The liquid metal thermal management system and thermal management method for an aircraft rudder shaft provided by the present invention realize cooling of the aircraft rudder shaft through heat exchange between a first heat dissipation medium and a second heat dissipation medium. Since the first heat dissipation medium is liquid metal, on the one hand, the boiling point of the liquid metal is usually greater than 1000°C, thereby avoiding the problems of heat transfer deterioration and reduced pipeline sealing reliability caused by gasification of the working medium in traditional water cooling technology; on the other hand, the thermal conductivity of the liquid metal is about 60 times that of water, and the convection heat transfer coefficient under the same conditions is more than one order of magnitude greater than that of water, thereby greatly improving the heat extraction efficiency of the aircraft rudder shaft; in addition, the liquid metal is stable in nature and can be reused. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 It is a structural schematic diagram of a liquid metal thermal management system for an aircraft rudder shaft provided by the present invention.

[0019] Figure 2 It is a cross-sectional view of the shell and tube heat exchanger provided by the present invention.

[0020] Figure 3It is a cross-sectional view of the partition wall heat exchanger provided by the present invention.

[0021] Reference numerals: 1. Aircraft rudder shaft; 2. Heat exchanger; 3. Drive pump; 4. Pressure vessel; 5. Controller; 6. Flow meter; 7. Temperature sensor network; 8. Flow regulator; 9. External environment; 21. Inner tube; 22. Outer ring. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limitations on the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0024] Combine the following Figure 1-Figure 3 The present invention describes a liquid metal thermal management system for an aircraft rudder shaft.

[0025] The first aspect of the present invention is to provide a liquid metal thermal management system for an aircraft rudder shaft, including a first subsystem and a second subsystem, wherein the first subsystem is a heat extraction circuit, including an aircraft rudder shaft 1, a heat exchanger 2 and a drive pump 3 connected in sequence; the aircraft rudder shaft 1, the heat exchanger 2 and the drive pump 3 form a closed loop. The drive pump 3 is used to drive a first heat dissipation medium; and the first heat dissipation medium of the first subsystem is liquid metal, or a mixture of liquid metals, such as a gallium indium tin alloy, with a melting point of 11°C.

[0026] The second subsystem includes a pressure vessel 4 and a heat exchanger 2. The pressure vessel 4 is connected to the upstream of the heat exchanger 2. The second heat dissipation medium in the second subsystem is a gaseous medium at normal temperature and pressure. The pressure vessel 4 is used to store the second heat dissipation medium, which is a gaseous medium at normal temperature and pressure, such as carbon dioxide, nitrogen, etc.

[0027] The heat exchanger 2 is used for heat exchange between the first heat dissipation medium and the second heat dissipation medium to achieve cooling of the aircraft rudder shaft 1 .

[0028] In the liquid metal thermal management system for the aircraft rudder shaft provided in this embodiment, the first heat dissipation working fluid adopts liquid metal, and a liquid metal mixed working fluid may also be adopted. On the one hand, since the boiling point of liquid metal is usually greater than 1000°C, the problems of heat transfer deterioration and reduced pipeline sealing reliability caused by gasification of the working fluid in water cooling technology are avoided; on the other hand, the thermal conductivity of liquid metal is about 60 times that of water, and the convective heat transfer coefficient under the same conditions is more than one order of magnitude greater than that of water, thereby greatly improving the heat extraction efficiency of the aircraft rudder shaft; in addition, liquid metal is stable in nature and can be reused.

[0029] In a preferred embodiment of the present invention, the first subsystem also includes a controller 5, a flow meter 6 and a temperature sensor network 7; the flow meter 6 is arranged between the heat exchanger 2 and the drive pump 3, and the flow meter 6 is used to measure the flow of the first heat dissipation medium in real time; the input end of the temperature sensor network 7 is connected to the aircraft rudder shaft 1, and the temperature sensor network 7 is used to collect temperature data of various parts of the aircraft rudder shaft 1; the output end of the temperature sensor network 7 is electrically connected to the controller 5, and the controller 5 is used to receive the temperature data.

[0030] The second subsystem further includes a flow regulator 8 and a controller 5. The flow regulator 8 is disposed between the pressure vessel 4 and the heat exchanger 2. The flow regulator 8 is used to regulate the flow of the second heat dissipating medium entering the heat exchanger 2. That is, the heat exchanger 2 and the controller 5 are shared by the first subsystem and the second subsystem.

[0031] The controller 5 is electrically connected to the flow meter 6, the drive pump 3, the temperature sensor network 7 and the flow regulator 8, and the controller 5 is used to adjust the flow meter 6 according to the temperature data and the flow of the first heat dissipation medium to adjust the flow of the first heat dissipation medium. The controller 5 adjusts the flow of the second heat dissipation medium based on the temperature data and the flow of the second heat dissipation medium. Through the above control method, a better cooling effect is achieved.

[0032] It should be noted that in Figure 1 In the figure, the solid arrows are the flow direction of the heat dissipation medium; the dotted arrows are the transmission direction of the electrical signal.

[0033] In a preferred embodiment of the present invention, the heat exchanger 2 is a shell-and-tube heat exchanger, which is provided with an inner tube 21 and an outer ring 22, wherein the inner tube 21 contains a first heat dissipation medium, and the outer ring 22 contains a second heat dissipation medium; and the outer ring 22 is connected to the external environment 9. During the heat exchange process, the second heat dissipation medium flows through the pressure vessel 4, the flow regulator 8 and the heat exchanger 2 in sequence, and is finally discharged into the external environment 9.

[0034] In a preferred embodiment of the present invention, the first heat dissipation medium includes gallium-based liquid metal or gallium-based alloy liquid metal, and the first heat dissipation medium may also be a liquid metal mixed medium, the liquid metal mixed medium is composed of liquid metal or other non-metallic liquid. The second heat dissipation medium includes one of carbon dioxide, nitrogen, ammonia and methane.

[0035] In a preferred embodiment of the present invention, the flow meter 6 includes an electromagnetic flow meter or an ultrasonic flow meter, and may also be other types of flow meters as long as flow measurement can be achieved.

[0036] In a preferred embodiment of the present invention, the driving pump 3 includes a DC conductive electromagnetic pump, an AC electromagnetic pump, a diaphragm pump or a piezoelectric pump. Other types of driving pumps may also be used, which are not specifically limited herein.

[0037] In a preferred embodiment of the present invention, the temperature sensor network 7 includes a wired sensor network and a wireless sensor network, as long as data transmission can be achieved.

[0038] In a preferred embodiment of the present invention, the pressure vessel 4 includes a storage pressure vessel or a reaction pressure vessel.

[0039] In one embodiment of the present invention, a liquid metal thermal management system for an aircraft rudder shaft is provided, wherein the first heat dissipation medium is a gallium indium tin alloy with a melting point of 11°C, the second heat dissipation medium is carbon dioxide, the driving pump 3 is a DC conductive electromagnetic pump, and the driving force is changed by changing the power supply current; the flow meter is an electromagnetic flow meter, which measures the flow of liquid metal in the heat extraction circuit in real time, and the sensor in the temperature sensing network is a K-type thermocouple. The pressure vessel is a small high-pressure gas cylinder, which stores carbon dioxide heat dissipation medium, and the flow regulator 8 can adjust the flow of carbon dioxide in real time.

[0040] like Figure 2 As shown, the heat exchanger 2 is a shell-and-tube heat exchanger, the inner tube 21 contains liquid titanium metal, the outer ring 22 contains carbon dioxide, and the controller 5 adjusts the flow rate of the first heat dissipation medium and the flow rate of the second heat dissipation medium according to the collected temperature data of various parts of the aircraft rudder shaft 1 and the flow data in the first subsystem.

[0041] When the above embodiment is in operation, the liquid metal in the first subsystem flows through the aircraft rudder shaft 1, the heat exchanger 2, the flow meter 6 and the drive pump 3 in sequence to form a heat extraction circuit, and the carbon dioxide in the second subsystem flows through the pressure vessel 4, the flow regulator 8 and the heat exchanger 2 in sequence, and is finally discharged into the external environment 9. The controller 5 receives the temperature data of each part of the aircraft rudder shaft 1 collected by the temperature sensor network 7 and the liquid metal flow data collected by the flow meter 6 in real time, and adjusts the current of the drive pump 3 in real time according to the temperature data to achieve this, and the flow regulation of carbon dioxide is achieved through the flow regulator 8.

[0042] Another embodiment of the present invention provides a liquid metal thermal management system for an aircraft rudder shaft, wherein the first heat dissipation medium is a bismuth indium tin alloy having a melting point of 60°C. To ensure the normal operation of the first subsystem, the pipeline needs to be heated and insulated, and the second heat dissipation medium is nitrogen. The driving pump 3 is a variable speed diaphragm pump, which changes the driving force by changing the power supply voltage. The flowmeter 6 is an ultrasonic flowmeter, which measures the flow of liquid metal in the heat extraction circuit in real time. The sensor in the temperature sensing network is a radiation thermometer. The pressure vessel 4 is a liquid nitrogen bottle, which stores nitrogen heat dissipation medium and is in liquid form in a high-pressure gas cylinder. The flow regulator 8 can adjust the flow of nitrogen in real time.

[0043] like Figure 3 As shown, the heat exchanger 2 is a partition-type heat exchanger, and the controller adjusts the heat dissipation medium flow in the two subsystems according to the collected temperature data of various parts of the aircraft rudder shaft and the flow data in subsystem 1.

[0044] When the above embodiment is in operation, the liquid metal in the first subsystem flows through the aircraft rudder shaft 1, the heat exchanger 2, the flow meter 6 and the drive pump 3 in sequence to form a heat extraction circuit, and the nitrogen in the second subsystem flows through the pressure vessel 4, the flow regulator 8 and the heat exchanger 2 in sequence, and is finally discharged into the external environment 9. The controller receives the temperature data of each part of the aircraft rudder shaft collected by the temperature sensor network 7 and the liquid metal flow data collected by the flow meter 6 in real time, and adjusts the liquid metal and nitrogen flow rates in real time according to the temperature data of each part of the aircraft rudder shaft 1. The flow rate of the liquid metal is adjusted by changing the voltage of the drive pump 3, and the flow rate of the nitrogen is adjusted by the flow regulator 8.

[0045] The liquid metal thermal management method for an aircraft rudder shaft provided by the present invention is described below. The liquid metal thermal management method for an aircraft rudder shaft described below and the liquid metal thermal management system for an aircraft rudder shaft described above can be referenced to each other.

[0046] A second aspect of the present invention provides a method for thermal management of liquid metal of an aircraft rudder shaft, using the thermal management system described in any one of the above embodiments, comprising: S1. A first heat dissipation medium flows in the first subsystem, and the first heat dissipation medium is used to remove heat from the aircraft rudder shaft 1, and the first heat dissipation medium in the heat removal circuit is liquid metal; S2. A second heat dissipation medium flows in the second subsystem, and the second heat dissipation medium is a gaseous medium at normal temperature and pressure; S3. The first heat dissipation medium and the second heat dissipation medium exchange heat through a heat exchanger.

[0047] The present invention realizes cooling of the aircraft rudder shaft 1 through heat exchange between a first heat dissipation medium and a second heat dissipation medium. Since the first heat dissipation medium is liquid metal, on the one hand, the boiling point of liquid metal is usually greater than 1000°C, which avoids the problems of heat transfer deterioration and reduced pipeline sealing reliability caused by gasification of the working medium in traditional water cooling technology; on the other hand, the thermal conductivity of liquid metal is about 60 times that of water, and the convection heat transfer coefficient under the same conditions is more than one order of magnitude greater than that of water, thereby greatly improving the heat extraction efficiency of the aircraft rudder shaft; in addition, liquid metal is stable in nature and can be reused.

[0048] In a feasible embodiment of the present invention, step S3 includes: S31, obtaining the surface temperature of the aircraft rudder shaft 1.

[0049] The surface temperature of each position of the aircraft rudder shaft 1 can be obtained through the temperature sensor network, which serves as a standard for the controller 5 to automatically control the flow of the first heat dissipation medium and the second heat dissipation medium. The temperature sensor network can be understood as a sensing device composed of multiple temperature sensors.

[0050] S32, monitoring the flow rate of the first heat dissipation medium in real time.

[0051] The flow rate of the first heat dissipation medium can be detected in real time by the flow meter 6. The flow meter 6 can be an electromagnetic flow meter or an ultrasonic flow meter, as long as it can detect the flow rate of the first heat dissipation medium and transmit it to the controller 5.

[0052] S33: Based on the surface temperature and the flow rate of the first heat dissipation fluid, adjust the flow rates of the first heat dissipation fluid and the second heat dissipation fluid.

[0053] The controller 5 can receive the surface temperature and the flow rate of the first heat dissipation fluid, and based on the surface temperature data and the flow rate data collected by the flowmeter 6, the controller 5 controls the flow rate of the first heat dissipation fluid by adjusting the voltage of the driving pump 3; the controller 5 controls the flow rate of the second heat dissipation fluid by adjusting the flow regulator 8, thereby achieving a better cooling effect.

[0054] In the liquid metal thermal management method of the aircraft rudder shaft provided by the present invention, the controller 5 can receive the temperature data and flow data in the first subsystem in real time, and the controller 5 adjusts the flow of the first heat dissipation fluid and the second heat dissipation fluid in real time according to the temperature data. The flow of the liquid metal is achieved by changing the voltage of the driving pump 3, and the flow of the second heat dissipation fluid is achieved by adjusting the regulator 8.

[0055] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0056] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "mode", "specific mode", or "some modes" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or mode are included in at least one embodiment or mode of the embodiment of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or mode. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or modes in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or modes described in this specification and the features of the different embodiments or modes, without contradiction.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A liquid metal thermal management system for an aircraft rudder shaft, characterized in that: comprising a first subsystem and a second subsystem; The first subsystem is a heat extraction circuit, comprising an aircraft rudder shaft (1), a heat exchanger (2), and a drive pump (3) connected in sequence; the drive pump (3) is used to drive a first heat dissipation medium; and the first heat dissipation medium of the first subsystem is liquid metal; The second subsystem comprises a pressure vessel (4) and the heat exchanger (2), the pressure vessel (4) being connected upstream of the heat exchanger (2); and the second heat dissipation medium in the second subsystem is a gaseous medium at normal temperature and pressure; the pressure vessel (4) is used to store the second heat dissipation medium; The heat exchanger (2) is used for heat exchange between the first heat dissipation medium and the second heat dissipation medium.

2. The liquid metal thermal management system for an aircraft rudder shaft according to claim 1, characterized in that: The first subsystem further comprises a controller (5), a flow meter (6) and a temperature sensor network (7); the flow meter (6) is arranged between the heat exchanger (2) and the drive pump (3), and the flow meter (6) is used to measure the flow rate of the first heat dissipation medium in real time; the input end of the temperature sensor network (7) is connected to the aircraft rudder shaft (1), and the temperature sensor network (7) is used to collect temperature data of various parts of the aircraft rudder shaft (1); The second subsystem further comprises a flow regulator (8) and the controller (5), wherein the flow regulator (8) is used to regulate the flow of the second heat dissipating medium; The controller (5) is electrically connected to the flow meter (6), the drive pump (3), the temperature sensor network (7) and the flow regulator (8), and the controller (5) is used to adjust the flow of the first heat dissipation fluid and the flow of the second heat dissipation fluid according to the temperature data and the flow of the first heat dissipation fluid.

3. The liquid metal thermal management system for an aircraft rudder shaft according to claim 1, characterized in that: The heat exchanger (2) is a shell-and-tube heat exchanger, provided with an inner tube (21) and an outer ring (22), wherein the inner tube (21) accommodates the first heat dissipation medium, and the outer ring (22) accommodates the second heat dissipation medium; and the outer ring (22) is in communication with an external environment (9).

4. The liquid metal thermal management system for an aircraft rudder shaft according to any one of claims 1 to 3, characterized in that: The first heat dissipation medium includes gallium-based liquid metal or gallium-based alloy liquid metal, and the second heat dissipation medium includes one of carbon dioxide, nitrogen, ammonia and methane.

5. The liquid metal thermal management system for an aircraft rudder shaft according to claim 2 or 3, characterized in that: The flow meter (6) comprises an electromagnetic flow meter or an ultrasonic flow meter.

6. The liquid metal thermal management system for an aircraft rudder shaft according to any one of claims 1 to 3, characterized in that: The driving pump (3) comprises a DC conduction electromagnetic pump, an AC electromagnetic pump, a diaphragm pump or a piezoelectric pump.

7. The liquid metal thermal management system for an aircraft rudder shaft according to any one of claims 1 to 3, characterized in that: The temperature sensor network (7) comprises a wired sensor network and a wireless sensor network.

8. The liquid metal thermal management system for an aircraft rudder shaft according to claim 1, characterized in that: The pressure vessel (4) includes a storage pressure vessel or a reaction pressure vessel.

9. A method for liquid metal thermal management of an aircraft rudder shaft, using the thermal management system according to any one of claims 1 to 8, characterized in that: include: A first heat dissipation medium flows in the first subsystem, the first heat dissipation medium is used to extract heat from the aircraft rudder shaft (1), and the first heat dissipation medium in the heat extraction circuit is liquid metal; A second heat dissipation medium flows in the second subsystem, and the second heat dissipation medium is a gaseous medium at normal temperature and pressure; The first heat dissipation medium and the second heat dissipation medium exchange heat through a heat exchanger.

10. The liquid metal thermal management method according to claim 9, characterized in that: The first subsystem and the second subsystem exchange heat through a heat exchanger including: Obtaining the surface temperature of the aircraft rudder shaft (1); Real-time monitoring of the flow rate of the first heat dissipation medium; Based on the surface temperature and the flow rate of the first heat dissipation fluid, the flow rates of the first heat dissipation fluid and the second heat dissipation fluid are adjusted.

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