Liquid metal thermal management system for aircraft rudder shafts and thermal management method

Abstract

The application provides a liquid metal heat management system and heat management method for an aircraft rudder shaft, the system comprising a first subsystem and a second subsystem; the first subsystem comprising an aircraft rudder shaft, a heat exchanger and a driving pump connected in sequence; and the first heat dissipation working medium of the first subsystem being a liquid metal; the second subsystem comprising a pressure container and a heat exchanger, and the second heat dissipation working medium in the second subsystem being a working medium in a gaseous state at normal temperature and pressure; and the heat exchanger being used for heat exchange between the first heat dissipation working medium and the second heat dissipation working medium. The liquid metal heat management system and heat management method for the aircraft rudder shaft provided by the application realize cooling of the aircraft rudder shaft through heat exchange between the first heat dissipation working medium and the second heat dissipation working medium; since the first heat dissipation working medium is a liquid metal, on the one hand, the boiling point of the liquid metal is usually greater than 1000 DEG C, which avoids problems such as heat transfer deterioration, reduction of pipeline sealing reliability and the like caused by gasification of the working medium in water cooling technology, and also provides heat extraction efficiency of the aircraft rudder shaft.

Description

Technical Field

[0001] This invention relates to the field of thermal management technology, and in particular to a liquid metal thermal management system and method for aircraft control shafts. Background Technology

[0002] When a high-speed aircraft enters or exits the atmosphere or continues to fly in space, it intensely compresses the air in front of it. This causes a violent viscous friction effect between the aircraft surface and air molecules, converting a large amount of molecular kinetic energy into heat energy. This causes the surface temperature of the aircraft to rise rapidly, a phenomenon known as aerodynamic heating. At lower speeds, the surface heat can be easily dissipated. However, when the speed exceeds Mach 2.5, the large amount of aerodynamic heat generated cannot be dissipated in time, causing the surface temperature of the aircraft to rise sharply. This can lead to a decrease in the strength of the airframe materials, deformation of the outer shell, or even loss of flight control, a phenomenon known as the thermal barrier.

[0003] Among the various thermal protection technologies for aircraft components, protective measures for the air rudder shaft are relatively limited. An air rudder consists of two parts: the shaft and the control surface. The control surface is located outside the aircraft, while the shaft, a fixed axis connecting the control surface and the aircraft body, is mostly located inside the aircraft. However, a section of the shaft connected to the control surface is directly exposed to the outside air. To ensure the reliability of control surface movement, thermal insulation material cannot be applied to this section of the shaft, placing high demands on its thermal protection. Active fluid cooling technology holds promise for significantly reducing the surface temperature of the shaft; currently, water-based active cooling technology is the primary approach.

[0004] However, under aerodynamic heating, the heat flux density on the exposed surface of the control shaft section outside the aircraft can exceed 1 MW / m². 2 The surface temperature reaches 700℃. Water-based active cooling technology suffers from problems such as deteriorated heat transfer due to working fluid vaporization and reduced pipeline sealing reliability. Summary of the Invention

[0005] This invention provides a liquid metal thermal management system and method for aircraft control shafts, which solves the defects of existing aircraft control shaft thermal protection measures that are simple and difficult to cope with the reduction in control shaft strength and reliability caused by high aerodynamic heat, and achieves efficient thermal protection for aircraft control shafts.

[0006] This invention provides a liquid metal thermal management system for an aircraft control shaft, comprising a first subsystem and a second subsystem;

[0007] The first subsystem is a heat extraction circuit, comprising an aircraft rudder shaft, a heat exchanger, and a drive pump connected in sequence; the drive pump is used to drive a first heat dissipation medium; and the first heat dissipation medium of the first subsystem is liquid metal.

[0008] The second subsystem includes a pressure vessel and the heat exchanger, with the pressure vessel connected upstream of the heat exchanger; and the second heat dissipation working fluid in the second subsystem is a gaseous working fluid at room temperature and pressure; the pressure vessel is used to store the second heat dissipation working fluid.

[0009] The heat exchanger is used for heat exchange between the first heat dissipation medium and the second heat dissipation medium.

[0010] According to the present invention, a liquid metal thermal management system for an aircraft control shaft is provided, wherein the first subsystem further includes a controller, a flow meter, and a temperature sensing network; the flow meter is disposed 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 sensing network is connected to the aircraft control shaft, and the temperature sensing network is used to collect temperature data of various parts of the aircraft control shaft.

[0011] The second subsystem also includes a flow regulator and the controller, wherein the flow regulator is used to regulate the flow rate of the second heat dissipation medium;

[0012] The controller is electrically connected to the flow meter, the drive pump, the temperature sensing network, and the flow regulator, and the controller is used to adjust the flow rate of the first heat dissipation medium and the flow rate of the second heat dissipation medium according to the temperature data and the flow rate of the first heat dissipation medium.

[0013] According to the present invention, a liquid metal thermal management system for an aircraft control shaft is provided, wherein the heat exchanger is a shell-and-tube heat exchanger having an inner tube and an outer ring, the inner tube containing a first heat dissipation medium and the outer ring containing a second heat dissipation medium; and the outer ring is in communication with the external environment.

[0014] According to the present invention, a liquid metal thermal management system for an aircraft control shaft is provided, wherein 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.

[0015] According to the present invention, a liquid metal thermal management system for an aircraft control shaft is provided, wherein the flow meter includes an electromagnetic flow meter or an ultrasonic flow meter.

[0016] According to the present invention, a liquid metal thermal management system for an aircraft rudder shaft is provided, wherein the drive pump includes a DC conductive electromagnetic pump, an AC electromagnetic pump, a diaphragm pump, or a piezoelectric pump.

[0017] According to the present invention, a liquid metal thermal management system for an aircraft control shaft is provided, wherein the temperature sensor network includes a wired sensor network and a wireless sensor network.

[0018] According to the present invention, a liquid metal thermal management system for an aircraft control shaft is provided, wherein the pressure vessel includes a storage pressure vessel or a reaction pressure vessel.

[0019] The present invention also provides a liquid metal thermal management method for an aircraft control shaft, utilizing the liquid metal thermal management system for an aircraft control shaft as described above, comprising:

[0020] A first heat dissipation medium circulates in the first subsystem. The first heat dissipation medium is used to heat the aircraft control shaft, and the first heat dissipation medium in the heat extraction circuit is liquid metal.

[0021] The second subsystem contains a second heat dissipation working fluid, which is a gaseous working fluid at normal temperature and pressure.

[0022] The first heat dissipation medium and the second heat dissipation medium exchange heat through a heat exchanger.

[0023] According to the liquid metal thermal management method for aircraft control shafts provided by the present invention, the first subsystem and the second subsystem exchange heat through a heat exchanger, including:

[0024] Obtain the surface temperature of the aircraft's control shaft;

[0025] Real-time monitoring of the flow rate of the first heat dissipation medium;

[0026] Based on the surface temperature and the flow rate of the first heat dissipation medium, the flow rates of the first heat dissipation medium and the second heat dissipation medium are adjusted.

[0027] The liquid metal thermal management system and method for aircraft control shafts provided by this invention achieve cooling of the aircraft control 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 liquid metal is usually greater than 1000℃, avoiding the problems of heat transfer deterioration and reduced pipeline sealing reliability caused by the vaporization 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 convective heat transfer coefficient under the same conditions is more than an order of magnitude greater than that of water, thus greatly improving the heat extraction efficiency of the aircraft control shaft; in addition, liquid metal is stable and can be reused. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0029] Figure 1This is a schematic diagram of the liquid metal thermal management system for the aircraft rudder shaft provided by the present invention.

[0030] Figure 2 This is a cross-sectional view of the shell-and-tube heat exchanger provided by the present invention.

[0031] Figure 3 This is a cross-sectional view of the indirect heat exchanger provided by the present invention.

[0032] Figure label:

[0033] 1. Aircraft control shaft; 2. Heat exchanger; 3. Drive pump; 4. Pressure vessel; 5. Controller; 6. Flow meter; 7. Temperature sensing network; 8. Flow regulator; 9. External environment; 21. Inner pipe; 22. Outer ring. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0035] In the description of the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0036] The following is combined Figures 1-3 The present invention describes a liquid metal thermal management system for aircraft rudder shafts.

[0037] A first aspect of this invention provides a liquid metal thermal management system for an aircraft control shaft, comprising a first subsystem and a second subsystem. The first subsystem is a heat extraction loop, comprising an aircraft control shaft 1, a heat exchanger 2, and a drive pump 3 connected in sequence; the aircraft control shaft 1, heat exchanger 2, and drive pump 3 form a closed loop. The drive pump 3 drives 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.

[0038] The second subsystem includes a pressure vessel 4 and a heat exchanger 2, with the pressure vessel 4 connected upstream of the heat exchanger 2. The second heat dissipation working fluid in the second subsystem is a gaseous working fluid at room temperature and pressure. The pressure vessel 4 is used to store the second heat dissipation working fluid, which is a gaseous working fluid at room temperature and pressure, such as carbon dioxide or nitrogen.

[0039] Heat exchanger 2 is used for heat exchange between the first and second heat dissipation working fluids to cool the aircraft rudder shaft 1.

[0040] The liquid metal thermal management system for the aircraft control shaft provided in this embodiment uses liquid metal as the first heat dissipation medium, or a mixture of liquid metals. On the one hand, since the boiling point of liquid metal is usually greater than 1000℃, the problems of heat transfer deterioration and reduced pipeline sealing reliability caused by the vaporization of the working medium 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 an order of magnitude greater than that of water, thus greatly improving the heat extraction efficiency of the aircraft control shaft. In addition, liquid metal is stable and can be reused.

[0041] In a preferred embodiment of the present invention, the first subsystem further includes a controller 5, a flow meter 6, and a temperature sensing network 7; the flow meter 6 is disposed between the heat exchanger 2 and the drive pump 3, and is used to measure the flow rate of the first heat dissipation medium in real time; the input end of the temperature sensing network 7 is connected to the aircraft rudder shaft 1, and the temperature sensing network 7 is used to collect temperature data of various parts of the aircraft rudder shaft 1; the output end of the temperature sensing network 7 is electrically connected to the controller 5, and the controller 5 is used to receive the temperature data.

[0042] The second subsystem also includes a flow regulator 8 and a controller 5. The flow regulator 8 is located between the pressure vessel 4 and the heat exchanger 2, and is used to regulate the flow rate of the second heat dissipation medium entering the heat exchanger 2. That is, the heat exchanger 2 and the controller 5 are shared by the first and second subsystems.

[0043] The controller 5 is electrically connected to the flow meter 6, the drive pump 3, the temperature sensing network 7, and the flow regulator 8. The controller 5 adjusts the flow meter 6 based on temperature data and the flow rate of the first heat dissipation medium to regulate the flow rate of the first heat dissipation medium. The controller 5 also adjusts the flow rate of the second heat dissipation medium based on temperature data and the flow rate of the second heat dissipation medium. Through these control methods, a superior cooling effect is achieved.

[0044] It should be noted that, in Figure 1 In the diagram, solid arrows indicate the flow direction of the heat dissipation medium; dashed arrows indicate the direction of electrical signal transmission.

[0045] In a preferred embodiment of the present invention, the heat exchanger 2 is a shell-and-tube heat exchanger, comprising an inner tube 21 and an outer ring 22. The inner tube 21 contains a first heat dissipation medium, and the outer ring 22 contains a second heat dissipation medium; the outer ring 22 is connected to the external environment 9. During the heat exchange process, the second heat dissipation medium flows sequentially through the pressure vessel 4, the flow regulator 8, and the heat exchanger 2, and is finally discharged into the external environment 9.

[0046] In a preferred embodiment of the present invention, the first heat dissipation medium comprises gallium-based liquid metal or gallium-based alloy liquid metal. The first heat dissipation medium may also be a liquid metal mixture, composed of liquid metal or other non-metallic liquids. The second heat dissipation medium comprises one of carbon dioxide, nitrogen, ammonia, and methane.

[0047] In a preferred embodiment of the present invention, the flow meter 6 includes an electromagnetic flow meter or an ultrasonic flow meter, or other types of flow meters, as long as they can measure the flow rate.

[0048] In a preferred embodiment of the present invention, the drive pump 3 includes a DC conductive electromagnetic pump, an AC electromagnetic pump, a diaphragm pump, or a piezoelectric pump. Other types of drive pumps may also be used, and no specific limitation is made here.

[0049] 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.

[0050] In a preferred embodiment of the present invention, the pressure vessel 4 includes a storage pressure vessel or a reaction pressure vessel.

[0051] In one embodiment of the present invention, a liquid metal thermal management system for an aircraft control shaft is provided. The first heat dissipation medium is a gallium indium tin alloy with a melting point of 11°C, and the second heat dissipation medium is carbon dioxide. The drive pump 3 is a DC conductive electromagnetic pump, which changes the driving force by changing the power supply current. The flow meter is an electromagnetic flow meter that measures the flow rate of the liquid metal in the heat extraction circuit in real time. The sensor in the temperature sensing network is a K-type thermocouple. The pressure vessel is a small high-pressure gas cylinder that stores the carbon dioxide heat dissipation medium, and the flow regulator 8 can adjust the flow rate of carbon dioxide in real time.

[0052] like Figure 2 As shown, heat exchanger 2 is a shell-and-tube heat exchanger. The inner tube 21 contains liquid titanium metal, and the outer ring 22 contains carbon dioxide. The controller 5 adjusts the flow rate of the first heat dissipation medium and the flow rate of the second heat dissipation medium based on the collected temperature data of various parts of the aircraft rudder shaft 1 and the flow data of the first subsystem.

[0053] In the above embodiment, during operation, the liquid metal in the first subsystem flows sequentially through the aircraft rudder shaft 1, heat exchanger 2, flow meter 6, and drive pump 3, forming a heat extraction loop. The carbon dioxide in the second subsystem flows sequentially through pressure vessel 4, flow regulator 8, and heat exchanger 2, and is finally discharged into the external environment 9. The controller 5 receives real-time temperature data from various parts of the aircraft rudder shaft 1 collected by the temperature sensor network 7 and liquid metal flow data collected by the flow meter 6. Based on the temperature data, it adjusts the current of the drive pump 3 in real-time. The flow regulation of carbon dioxide is achieved through the flow regulator 8.

[0054] Another embodiment of the present invention provides a liquid metal thermal management system for an aircraft control shaft. The first heat dissipation medium is a bismuth-indium-tin alloy with a melting point of 60°C. To ensure the normal operation of the first subsystem, the pipeline needs to be heated and insulated. The second heat dissipation medium is nitrogen. The drive pump 3 is a variable-speed diaphragm pump, which changes the driving force by altering the supply voltage. The flow meter 6 is an ultrasonic flow meter that measures the flow rate of the 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 cylinder that stores nitrogen as the heat dissipation medium, which is in a liquid state within the high-pressure cylinder. The flow regulator 8 can adjust the nitrogen flow rate in real time.

[0055] like Figure 3 As shown, heat exchanger 2 is a partitioned heat exchanger. The controller adjusts the flow rate of the heat dissipation medium in the two subsystems based on the collected temperature data of various parts of the aircraft rudder shaft and the flow data in subsystem one.

[0056] In the above embodiment, during operation, the liquid metal in the first subsystem flows sequentially through the aircraft rudder shaft 1, heat exchanger 2, flow meter 6, and drive pump 3, forming a heat extraction loop. In the second subsystem, nitrogen flows sequentially through pressure vessel 4, flow regulator 8, and heat exchanger 2, and is finally discharged into the external environment 9. The controller receives in real time temperature data from various parts of the aircraft rudder shaft collected by the temperature sensor network 7 and liquid metal flow data collected by the flow meter 6. Based on the temperature data of various parts of the aircraft rudder shaft 1, the controller adjusts the flow rates of liquid metal and nitrogen in real time. The flow rate adjustment of liquid metal is achieved by changing the voltage of drive pump 3, and the flow rate adjustment of nitrogen is achieved by flow regulator 8.

[0057] The liquid metal thermal management method for aircraft rudder shafts provided by the present invention will be described below. The liquid metal thermal management method for aircraft rudder shafts described below can be referred to in correspondence with the liquid metal thermal management system for aircraft rudder shafts described above.

[0058] A second aspect of the present invention provides a liquid metal thermal management method for an aircraft control shaft, utilizing the thermal management system described in any of the preceding embodiments, comprising:

[0059] S1. A first heat dissipation medium flows through the first subsystem. The first heat dissipation medium is used to heat the aircraft rudder shaft 1, and the first heat dissipation medium in the heat extraction circuit is liquid metal.

[0060] S2. A second heat dissipation working fluid circulates in the second subsystem. The second heat dissipation working fluid is a gaseous working fluid at normal temperature and pressure.

[0061] S3, the first heat dissipation medium and the second heat dissipation medium exchange heat through a heat exchanger.

[0062] This invention achieves 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℃, avoiding the problems of heat transfer deterioration and reduced pipeline sealing reliability caused by the vaporization 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 convective heat transfer coefficient under the same conditions is more than an order of magnitude greater than that of water, thus greatly improving the heat extraction efficiency of the aircraft rudder shaft; in addition, liquid metal is stable and can be reused.

[0063] In a feasible embodiment of the present invention, step S3 includes:

[0064] S31. Obtain the surface temperature of the aircraft rudder shaft 1.

[0065] The surface temperature of various locations on the aircraft's control shaft 1 can be obtained through a temperature sensing network, serving as a standard for the controller 5 to automatically adjust the flow rates of the first and second heat dissipation media. The temperature sensing network can be understood as a sensing device composed of multiple temperature sensors.

[0066] S32. Real-time monitoring of the flow rate of the first heat dissipation medium.

[0067] 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 the data to the controller 5.

[0068] S33. Adjust the flow rates of the first and second heat dissipation media based on the surface temperature and the flow rate of the first heat dissipation media.

[0069] The controller 5 can receive the surface temperature and the flow rate of the first heat dissipation medium. Based on the surface temperature data and the flow rate data collected by the flow meter 6, the controller 5 controls the flow rate of the first heat dissipation medium by adjusting the voltage of the drive pump 3. The controller 5 controls the flow rate of the second heat dissipation medium by adjusting the flow regulator 8, which can achieve a better cooling effect.

[0070] In the liquid metal thermal management method for aircraft control shafts provided by the present invention, the controller 5 can receive temperature data and flow data in the first subsystem in real time. Moreover, the controller 5 adjusts the flow rates of the first and second heat dissipation working fluids in real time according to the temperature data. The flow rate of the liquid metal is achieved by changing the voltage of the drive pump 3, and the flow rate of the second heat dissipation working fluid is achieved by adjusting the regulator 8.

[0071] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention according to the specific circumstances.

[0072] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "method," "specific method," or "some methods," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or method is included in at least one embodiment or method of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or method. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or methods. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or methods described in this specification, as well as the features of different embodiments or methods.

[0073] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate 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 control shaft, characterized in that, Includes the first subsystem and the second subsystem; 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 drive pump (3) is used to drive the first heat dissipation medium; and the first heat dissipation medium of the first subsystem is liquid metal; The second subsystem includes 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 working fluid in the second subsystem is a gaseous working fluid at room temperature and pressure; the pressure vessel (4) is used to store the second heat dissipation working fluid; The heat exchanger (2) is used for heat exchange between the first heat dissipation medium and the second heat dissipation medium; The first subsystem also includes a controller (5), a flow meter (6), and a temperature sensing network (7); the flow meter (6) is located 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 sensing network (7) is connected to the aircraft rudder shaft (1), and the temperature sensing network (7) is used to collect temperature data of various parts of the aircraft rudder shaft (1); The second subsystem also includes a flow regulator (8) and the controller (5), wherein the flow regulator (8) is used to regulate the flow rate of the second heat dissipation medium; The controller (5) is electrically connected to the flow meter (6), the drive pump (3), the temperature sensing network (7) and the flow regulator (8), and the controller (5) is used to adjust the flow rate of the first heat dissipation medium and the flow rate of the second heat dissipation medium according to the temperature data and the flow rate of the first heat dissipation medium.

2. The liquid metal thermal management system for aircraft control shafts according to claim 1, characterized in that, The heat exchanger (2) is a shell-and-tube heat exchanger, which has an inner tube (21) and an outer ring (22). The inner tube (21) contains the first heat dissipation medium, and the outer ring (22) contains the second heat dissipation medium. The outer ring (22) is connected to the external environment (9).

3. The liquid metal thermal management system for an aircraft control shaft according to any one of claims 1-2, 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.

4. The liquid metal thermal management system for aircraft control shafts according to claim 2, characterized in that, The flow meter (6) includes an electromagnetic flow meter or an ultrasonic flow meter.

5. The liquid metal thermal management system for an aircraft control shaft according to any one of claims 1-2, characterized in that, The drive pump (3) includes a DC conductive electromagnetic pump, an AC electromagnetic pump, a diaphragm pump, or a piezoelectric pump.

6. The liquid metal thermal management system for an aircraft control shaft according to any one of claims 1-2, characterized in that, The temperature sensor network (7) includes a wired sensor network and a wireless sensor network.

7. The liquid metal thermal management system for aircraft control shafts according to claim 1, characterized in that, The pressure vessel (4) includes a storage pressure vessel or a reaction pressure vessel.

8. A liquid metal thermal management method for an aircraft control shaft, utilizing the thermal management system described in any one of claims 1-7, characterized in that, include: A first heat dissipation medium circulates in the first subsystem. The first heat dissipation medium is used to heat the aircraft rudder shaft (1), and the first heat dissipation medium in the heat dissipation circuit is liquid metal. The second subsystem contains a second heat dissipation working fluid, which is a gaseous working fluid at normal temperature and pressure. The first heat dissipation medium and the second heat dissipation medium exchange heat through a heat exchanger; obtain the surface temperature of the aircraft rudder shaft (1); monitor the flow rate of the first heat dissipation medium in real time; and adjust the flow rates of the first heat dissipation medium and the second heat dissipation medium based on the surface temperature and the flow rate of the first heat dissipation medium.

Images