A liquid metal heat pipe and heat dissipation device applied to the space microgravity environment

Abstract

The present invention relates to the technical field of heat dissipation, and provides a liquid metal heat pipe and a heat dissipation device applied to a space microgravity environment. The above-mentioned liquid metal heat pipe includes: a pipe shell, a wick, and liquid metal; the wick and the liquid metal are arranged inside the pipe shell, and a steam flow channel penetrating axially along the pipe shell is formed inside the wick; the wick includes a first sintered wick, a micro-groove wick, and a second sintered wick connected in sequence along the axial direction of the pipe shell; both the first sintered wick and the second sintered wick include a plurality of copper meshes sleeved from the inside to the outside in sequence; the micro-groove wick includes a plurality of liquid absorption flow channels extending along the axial direction of the pipe shell, and the inner wall of the liquid absorption flow channel is provided with a groove structure extending along the axial direction of the pipe shell. The liquid metal heat pipe of the present invention can normally perform heat dissipation work in a space microgravity environment, and has good anti-gravity heat transfer performance, which helps to improve the heat dissipation efficiency of satellite equipment and enhance its reliability and stability in the space environment.

Description

Technical Field

[0001] The present invention relates to the technical field of heat dissipation, and particularly to a liquid metal heat pipe and a heat dissipation device applied to a space microgravity environment. Background Art

[0002] A heat pipe is an efficient passive heat transfer device that uses the phase change of a working fluid for heat transfer and has advantages such as high heat transfer efficiency, excellent isothermal performance, simple processing and manufacturing, simple physical structure, and convenient installation and maintenance.

[0003] However, in practical applications, existing heat pipes are usually applied to ground environments. In a space microgravity environment, traditional convection and natural convection heat dissipation methods are no longer effective, and it is difficult to ensure the anti-gravity heat transfer performance of the heat pipe. Therefore, for a space microgravity environment, developing a heat pipe that can achieve efficient heat dissipation is crucial for maintaining the temperature stability of satellite equipment. Summary of the Invention

[0004] The present invention provides a liquid metal heat pipe and a heat dissipation device applied to a space microgravity environment to at least solve or improve the problem that it is difficult for existing heat pipes to ensure anti-gravity heat transfer performance when applied in a space microgravity environment.

[0005] In a first aspect, the present invention provides a liquid metal heat pipe applied to a space microgravity environment, including: a tube shell, a wick, and a liquid metal;

[0006] The wick and the liquid metal are arranged inside the tube shell, and a vapor flow channel penetrating axially along the tube shell is formed inside the wick; the wick includes a first sintered wick, a micro-grooved wick, and a second sintered wick that are sequentially connected along the axial direction of the tube shell;

[0007] Both the first sintered wick and the second sintered wick include a plurality of copper meshes sleeved sequentially from the inside out; the micro-grooved wick includes a plurality of liquid absorption channels extending along the axial direction of the tube shell, and the inner wall of the liquid absorption channel is provided with a groove structure extending along the axial direction of the tube shell;

[0008] The liquid metal heat pipe has an evaporation end and a condensation end. The liquid metal evaporates into a gas at the evaporation end and can reach the condensation end along the vapor flow channel. The liquid metal condenses into a liquid at the condensation end and sequentially returns to the evaporation end along the second sintered wick, the micro-grooved wick, and the first sintered wick.

[0009] According to the liquid metal heat pipe applied to a space microgravity environment provided by the present invention, both the first sintered wick and the first sintered wick include a plurality of sequentially connected liquid absorption sections;

[0010] Along the direction from the evaporation end to the condensation end, the porosity of the plurality of liquid absorption sections corresponding to the first sintered liquid absorption core gradually increases, and the porosity of the plurality of liquid absorption sections corresponding to the second sintered liquid absorption core gradually decreases.

[0011] According to a liquid metal heat pipe applied to the space microgravity environment provided by the present invention, the micro-groove liquid absorption core includes a plurality of liquid absorption tubes, and the plurality of liquid absorption tubes are arranged in a cylindrical shape, and a liquid absorption flow channel is formed in each liquid absorption tube.

[0012] According to a liquid metal heat pipe applied to the space microgravity environment provided by the present invention, the tube shell is a metal shell, and a nano-porous copper powder layer prepared by sintered nano-porous copper powder is provided on the inner wall of the metal shell, and the inner wall of the nano-porous copper powder layer is in contact with the peripheral wall of the liquid absorption core.

[0013] According to a liquid metal heat pipe applied to the space microgravity environment provided by the present invention, the metal copper mesh is obtained by sintering irregular copper powder.

[0014] According to a liquid metal heat pipe applied to the space microgravity environment provided by the present invention, the liquid metal is a bismuth-based metal.

[0015] In a second aspect, the present invention further provides a heat dissipation device, including: a heat collecting plate, a heat dissipation plate, and the liquid metal heat pipe applied to the space microgravity environment as described above;

[0016] The evaporation end of the liquid metal heat pipe is connected to the heat collecting plate, and the condensation end of the liquid metal heat pipe is connected to the heat dissipation plate.

[0017] According to a heat dissipation device provided by the present invention, the central axis of the liquid metal heat pipe is inclined with respect to the plate surface of the heat dissipation plate.

[0018] According to a heat dissipation device provided by the present invention, the heat dissipation device further includes a circulation channel and an electromagnetic pump; the circulation channel is connected between the evaporation end and the condensation end of the liquid metal heat pipe; the electromagnetic pump is used to drive the liquid metal to flow from the condensation end along the circulation channel to the evaporation end.

[0019] According to a heat dissipation device provided by the present invention, the heat dissipation device further includes a temperature sensor and a control module; the temperature sensor and the control module are electrically connected, and the control module and the electromagnetic pump are electrically connected;

[0020] The temperature sensor is arranged on the heat collecting plate and is used to detect the temperature information of the heat collecting plate, and the control module is used to control the working state of the electromagnetic pump according to the temperature information fed back by the temperature sensor.

[0021] The liquid metal heat pipe and heat dissipation device applied to the space microgravity environment provided by the present invention configures the wick of the liquid metal heat pipe as a first sintered wick, a micro-groove wick, and a second sintered wick connected in sequence. Both the first sintered wick and the second sintered wick have the characteristics of high capillary pumping pressure but relatively low liquid permeability, while the micro-groove wick has the characteristics of low capillary pumping pressure but relatively high liquid permeability. This enables the wick to better balance the contradiction between high capillary ability and high permeability, and can simultaneously obtain relatively high capillary suction and evaporation efficiency, while achieving low flow resistance and radial heat conduction. When this design is applied in a liquid metal heat pipe, it can ensure that the liquid metal heat pipe can normally dissipate heat in the space microgravity environment and has good anti-gravity heat transfer performance, which helps to improve the heat dissipation efficiency of satellite equipment and enhance its reliability and stability in the space environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0023] Figure 1 is a schematic structural diagram of the liquid metal heat pipe provided by the present invention;

[0024] Figure 2 is a schematic cross-sectional structure diagram of the wick provided by the present invention;

[0025] Figure 3 is a schematic structural diagram of a single-piece metal copper mesh provided by the present invention;

[0026] Figure 4 is a physical image of the outer surface of the first sintered wick provided by the present invention;

[0027] Figure 5 is a physical image of the inner section of the first sintered wick provided by the present invention;

[0028] Figure 6 is a schematic structural diagram of a single wick tube provided by the present invention;

[0029] Reference numerals:

[0030] 1, tube shell; 2, wick

[0031] 21. First sintered wick; 22. Micro-grooved wick; 23. Second sintered wick; 20. Vapor flow channel; 201. Evaporation end; 202. Condensation end; 211. Copper mesh; 221. Liquid absorption tube; 2211. Liquid absorption flow channel; 2212. Groove structure. Detailed implementation manners

[0032] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention. Apparently, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art without making creative efforts based on the embodiments in the present invention belong to the scope of protection of the present invention.

[0033] The following Figures 1 - 6 , through specific embodiments and their application scenarios, will provide a detailed description of the liquid metal heat pipe and heat dissipation device applied to the space microgravity environment provided by the embodiments of the invention.

[0034] In a first aspect, as Figure 1 and Figure 2 shown, an embodiment of the present invention provides a liquid metal heat pipe applied to a space microgravity environment, including: a tube shell 1, a wick 2, and liquid metal;

[0035] The wick 2 and the liquid metal are arranged inside the tube shell 1, and a vapor flow channel 20 penetrating axially along the tube shell 1 is formed inside the wick 2; the wick 2 includes a first sintered wick 21, a micro-grooved wick 22, and a second sintered wick 23 that are sequentially connected along the axis of the tube shell 1; both the first sintered wick 21 and the second sintered wick 23 include a plurality of copper meshes 211 sleeved from the inside to the outside in sequence; the micro-grooved wick 22 includes a plurality of liquid absorption flow channels 2211 extending axially along the tube shell 1, and the inner wall of the liquid absorption flow channel 2211 is provided with a groove structure 2212 extending axially along the tube shell 1;

[0036] The liquid metal heat pipe has an evaporation end 201 and a condensation end 202. The liquid metal evaporates into a gas state at the evaporation end 201, and the gaseous liquid metal can reach the condensation end 202 along the vapor flow channel 20. The liquid metal condenses into a liquid state at the condensation end 202, and the liquid liquid metal can sequentially return to the evaporation end 201 along the second sintered wick 23, the micro-grooved wick 22, and the first sintered wick 21. Among them, Figure 2 different arrows are used to respectively indicate the flow directions of the gaseous liquid metal and the liquid liquid metal along the wick 2.

[0037] It is understandable that the shell 1 is in a closed shape, the wick 2 is in a cylindrical shape, the shell 1 is in a cylindrical shape, the wick 2 is arranged inside the shell 1 and coaxially with the shell 1; the peripheral wall of the wick 2 is in contact with the inner side wall of the shell 1. The first end of the shell 1 serves as the evaporation end 201 of the liquid metal heat pipe and is configured to be connected to the heat source in the satellite equipment, and the second end of the shell 1 serves as the condensation end 202 of the liquid metal heat pipe and is configured to be connected to the corresponding cold source in the satellite equipment.

[0038] The shell 1 can be arranged to extend in a straight line or in a curve, and no specific limitation is made thereto. Among them, the shell 1 is usually configured to be straight in actual applications.

[0039] Meanwhile, a first cavity for storing liquid metal is provided between the first end of the shell 1 and the end of the first sintered wick 21 away from the micro-groove wick 22, and a second cavity for storing liquid metal is provided between the second end of the shell 1 and the end of the second sintered wick 23 away from the micro-groove wick 22. Among them, the liquid metal can be selected from sodium, potassium, lithium, etc.

[0040] Since the wick 2 is provided with a vapor flow channel 20, the wick 2 can be specifically configured to be cylindrical; correspondingly, the vapor flow channel 20 sequentially penetrates through the first sintered wick 21, the micro-groove wick 22 and the second sintered wick 23, and the first sintered wick 21, the micro-groove wick 22 and the second sintered wick 23 can all be configured to be cylindrical.

[0041] Among them, Figure 3 schematically shows the structure of the single-piece metal copper mesh 211. The single-piece metal copper mesh 211 is constructed into a cylindrical shape, and then a plurality of cylindrical metal copper meshes 211 are sequentially arranged from the inside to the outside, and sintered and rolled to prepare the first sintered wick 21 or the second sintered wick 23. Figure 4 and Figure 5 respectively schematically show the physical images of the outer surface and the inner section of the first sintered wick 21 obtained by electron microscope scanning.

[0042] When the liquid metal heat pipe is working, the evaporation end 201 absorbs heat from the heat source, and the liquid metal absorbs heat and evaporates, so that the gaseous liquid metal enters the vapor flow channel 20. Due to the condensation of the vapor at the condensation end 202, the gaseous liquid metal condenses into a liquid and releases heat, which creates a pressure difference between the evaporation end 201 and the condensation end 202. Under the action of the pressure difference, the gaseous liquid metal travels from the evaporation end 201 to the condensation end 202 along the vapor flow channel 20; under the capillary action of the wick 2, the liquid liquid metal returns to the evaporation end 201 successively along the voids in the second sintered wick 23, along the liquid suction flow channels 2211 in the micro-groove wick 22, and along the voids in the first sintered wick 21, and is heated and evaporated again under the action of the heat source, thus completing a phase change process of the liquid metal and being able to flow reciprocally along this circulation path. The above cycle realizes the heat transfer of the liquid metal heat pipe from the evaporation end 201 to the condensation end 202.

[0043] Since the wick 2 of the liquid metal heat pipe is composed of the first sintered wick 21, the micro-groove wick 22 and the second sintered wick 23, both the first sintered wick 21 and the second sintered wick 23 have the characteristics of high capillary pumping pressure but relatively low liquid permeability, while the micro-groove wick 22 has the characteristics of low capillary pumping pressure but relatively high liquid permeability. This enables the wick 2 to better balance the contradiction between high capillary ability and high permeability, and can simultaneously obtain relatively high capillary suction force and evaporation efficiency, while realizing low flow resistance and radial heat conduction. When this design is applied in the liquid metal heat pipe, it can ensure that the liquid metal heat pipe can normally dissipate heat in the space microgravity environment and has good anti-gravity heat transfer performance, which helps to improve the heat dissipation efficiency of satellite equipment and enhance its reliability and stability in the space environment.

[0044] In some embodiments, as Figure 2 shown, both the first sintered wick 21 and the first sintered wick 21 include a plurality of successively connected liquid suction segments;

[0045] Along the direction from the evaporation end 201 to the condensation end 202, the porosity of the plurality of liquid suction segments corresponding to the first sintered wick 21 gradually increases, and the porosity of the plurality of liquid suction segments corresponding to the second sintered wick 23 gradually decreases.

[0046] It can be understood that for the first sintered wick 21 or the first sintered wick 21, each liquid suction segment is successively connected along the axial direction of the tube shell 1, and each liquid suction segment is composed of a plurality of cylindrical metal copper meshes 211 arranged successively from the inside to the outside. By selecting metal copper meshes 211 with different weaving densities for different liquid suction segments, the first sintered wick 21 and the first sintered wick 21 required by the present invention can be prepared.

[0047] By setting the porosity of the first sintered wick 21 and each wicking section corresponding to the first sintered wick 21, it is ensured that the gaseous liquid metal at the evaporation end 201 flows from the evaporation end 201 to the condensation end 202 along the vapor flow channel 20, and the contradiction between the high capillary ability and high permeability of the wick 2 is better balanced. It is ensured that the liquid liquid metal at the condensation end 202 can make good use of the capillary suction to flow from the condensation end 202 to the evaporation end 201 along the wick 2, and there will be no significant mutual interference between these two flow directions of the liquid metal, thereby optimizing the anti-gravity heat transfer performance of the liquid metal heat pipe and improving the ultimate power of the liquid metal heat pipe heat transfer.

[0048] Optionally, both the first sintered wick 21 and the first sintered wick 21 include two successively connected wicking sections. The porosity range of the wicking section closer to the micro-grooved wick 22 is 87%-97%. For example, the porosity can specifically be 87%, 90%, 92%, 95%, 97%, etc.; at the same time, the porosity range of the wicking section farther from the micro-grooved wick 22 is 75%-85%. For example, the porosity can specifically be 75%, 78%, 80%, 83%, 85%, etc.

[0049] In some embodiments, as Figure 2 and Figure 6 shown, the micro-grooved wick 22 includes a plurality of wicking tubes 221. The plurality of wicking tubes 221 are arranged in a cylindrical shape, and a wicking flow channel 2211 is formed in each wicking tube 221.

[0050] Specifically, the wicking tube 221 includes a first half tube and a second half tube; the first half tube and the second half tube can be assembled to form the wicking tube 221. A wicking flow channel 2211 is formed between the first half tube and the second half tube. The inner walls of the first half tube and the second half tube are both provided with a plurality of groove structures 2212 extending along the axial direction of the tube shell 1. The groove structures 2212 can better guide the liquid metal to flow along the wicking flow channel 2211 and provide capillary force for the flow of the liquid metal.

[0051] Exemplarily, the cross-section of the wicking tube 221 is rectangular. Both the first half tube and the second half tube are in a groove-like structure. The two groove edges of the first half tube are connected to the two groove edges of the second half tube in one-to-one correspondence, so that the first half tube and the second half tube are assembled to form the wicking tube 221.

[0052] Among them, the bottom of the first half tube and the bottom of the second half tube are both provided with a plurality of protrusions arranged side by side. Each protrusion extends along the length direction of the wicking tube 221, and a groove structure 2212 is formed between two adjacent protrusions.

[0053] In some embodiments, the shell 1 is a metal shell. For example, the metal shell can be a copper shell. The inner wall of the metal shell is provided with a nano-porous copper powder layer prepared by sintered nano-porous copper powder, and the inner wall of the nano-porous copper powder layer is in contact with the peripheral wall of the liquid absorption core 2.

[0054] It can be understood that nano-porous copper powder is a material with a unique microstructure, which is characterized by containing a large number of micropores. The porosity of nano-porous copper powder is usually between 20% and 80%.

[0055] Due to the porous structure of the nano-porous copper powder, the nano-porous copper powder layer prepared from the nano-porous copper powder has good thermal conductivity, so that the radial heat conduction and heat dissipation effects of the liquid metal heat pipe can be ensured by using the nano-porous copper powder layer.

[0056] In some embodiments, the metal copper mesh 211 is obtained by sintering irregular copper powder.

[0057] It can be understood that irregular copper powder is a kind of copper powder with irregular morphology, its particle shape is irregular and its size is different. The particle size distribution of irregular copper powder is relatively wide, usually ranging from a few microns to several hundred microns. The density of irregular copper powder is close to the density of pure copper, about 8.96 g / cm³.

[0058] Thus, using sintered irregular copper powder to prepare the metal copper mesh 211 can ensure the thermal conductivity of the metal copper mesh 211, and further optimize the anti-gravity heat transfer performance of the liquid metal heat pipe.

[0059] In some embodiments, the liquid metal is a bismuth-based metal.

[0060] It can be understood that the liquid metal heat pipe uses the phase change of the liquid metal for heat transfer. Due to the characteristics of bismuth-based metals such as high electrical conductivity, high thermal conductivity, low viscosity and wide liquid temperature range, by selecting the liquid metal as a bismuth-based metal, efficient convective heat transfer and solid-liquid phase change heat control effects can be achieved in the space microgravity environment.

[0061] In a second aspect, the present invention also provides a heat dissipation device, including: a heat collecting plate, a heat dissipating plate and the liquid metal heat pipe applied to the space microgravity environment as described above; the evaporation end 201 of the liquid metal heat pipe is connected to the heat collecting plate, and the condensation end 202 of the liquid metal heat pipe is connected to the heat dissipating plate.

[0062] It can be understood that both the heat collecting plate and the heat dissipating plate can be made of metals with good thermal conductivity. The heat collecting plate is configured to be connected to the heat source in the sanitary equipment, and the heat dissipating plate is connected to the corresponding cold source of the satellite equipment. For example, the heat dissipating plate can be directly exposed to the space environment on the side facing away from the sun.

[0063] Heat transfer between the heat collection plate and the heat dissipation plate through the liquid metal heat pipe can effectively manage and disperse the heat generated by the heat source inside the satellite equipment, maintain the temperature stability inside the satellite equipment under extreme temperature conditions, reduce equipment failures caused by overheating, lower the maintenance cost and frequency of the satellite equipment, improve the reliability and service life of the satellite equipment, and contribute to further reducing the operating cost of the space mission.

[0064] In some embodiments, as Figure 1 shown, the central axis of the liquid metal heat pipe is inclined with respect to the plate surface of the heat dissipation plate.

[0065] Specifically, the included angle between the central axis of the liquid metal heat pipe and the plate surface of the heat dissipation plate is α, and the value range of α is 80º to 90º. For example, the specific values of α are 80º, 85º, 90º, etc. This design not only ensures that the liquid metal heat pipe can adapt to the internal structure of the satellite equipment for spatial layout, but also facilitates the reflux of the liquid metal along the wick 2 from the condensation end 202 to the evaporation end 201, realizing that the heat transfer limit power of the liquid metal heat pipe under completely anti-gravity conditions (the inclination angle α is 90°) is as high as 90W.

[0066] In some embodiments, the heat dissipation device further includes a circulation channel and an electromagnetic pump; the circulation channel is connected between the evaporation end 201 and the condensation end 202 of the liquid metal heat pipe; the electromagnetic pump is used to drive the liquid metal to flow from the condensation end 202 along the circulation channel to the evaporation end 201.

[0067] It can be understood that in practical applications, the use of the electromagnetic pump can effectively drive the flow of the liquid metal in the microgravity environment, ensure that it can flow quickly and fill the liquid metal heat pipe during startup, and realize the rapid startup of the liquid metal heat pipe from the frozen state to the normal working state.

[0068] During the operation of the liquid metal heat pipe, by driving the liquid metal to flow from the condensation end 202 along the circulation channel towards the evaporation end 201 through the electromagnetic pump, the flow and phase change process of the liquid metal can also be precisely controlled, realizing the control of the working state of the liquid metal heat pipe.

[0069] Furthermore, in order to precisely control the working state of the liquid metal heat pipe, the heat dissipation device further includes a temperature sensor and a control module; the temperature sensor and the control module are electrically connected, and the control module and the electromagnetic pump are electrically connected;

[0070] The temperature sensor is arranged on the heat collection plate and is used to detect the temperature information of the heat collection plate. The control module is used to control the working state of the electromagnetic pump according to the temperature information fed back by the temperature sensor.

[0071] Specifically, the control module can be a PLC controller or a central processing unit. Multiple temperature sensors can be provided, and the multiple temperature sensors are arranged in different areas of the heat collecting plate. This design can detect the temperature change of the heat source in real time based on the multiple temperature sensors. The control module can accurately calculate the temperature of the heat source according to the information fed back by the multiple temperature sensors, and adaptively control the working state of the electromagnetic pump according to the temperature of the heat source, so as to realize the intelligent regulation of the working state of the liquid metal heat pipe.

[0072] 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 them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A liquid metal heat pipe for use in a space microgravity environment, characterized in that: include: Tube shell, wick and liquid metal; The wick and the liquid metal are arranged in the tube shell, and a steam flow channel is formed in the wick that runs through the tube shell in the axial direction; the wick includes a first sintered wick, a micro-groove wick and a second sintered wick that are sequentially connected in the axial direction of the tube shell; The first sintered liquid absorbent core and the second sintered liquid absorbent core both include a plurality of metal copper meshes sequentially sleeved from the inside to the outside; the micro-groove liquid absorbent core includes a plurality of liquid absorption channels extending along the axial direction of the tube shell, and the inner wall of the liquid absorption channel is provided with a groove structure extending along the axial direction of the tube shell; The liquid metal heat pipe has an evaporation end and a condensation end. The liquid metal evaporates into a gas at the evaporation end and can reach the condensation end along the steam flow channel. The liquid metal condenses into a liquid at the condensation end and can return to the evaporation end along the second sintered liquid wick, the micro-groove liquid wick and the first sintered liquid wick in sequence.

2. The liquid metal heat pipe for use in a space microgravity environment according to claim 1, characterized in that: The first sintered liquid absorbent core and the second sintered liquid absorbent core each include a plurality of liquid absorbent sections connected in sequence; Along the direction from the evaporation end to the condensation end, the porosity of the plurality of liquid absorbing sections corresponding to the first sintered liquid absorbing core gradually increases, and the porosity of the plurality of liquid absorbing sections corresponding to the second sintered liquid absorbing core gradually decreases.

3. The liquid metal heat pipe for use in a space microgravity environment according to claim 1, characterized in that: The micro-groove liquid-absorbing core comprises a plurality of liquid-absorbing tubes, which are arranged in a cylindrical shape, and the liquid-absorbing flow channel is formed in each of the liquid-absorbing tubes.

4. The liquid metal heat pipe for use in a space microgravity environment according to any one of claims 1 to 3, characterized in that: The tube shell is a metal shell, the inner wall of the metal shell is provided with a nanoporous copper powder layer prepared by sintering nanoporous copper powder, and the inner wall of the nanoporous copper powder layer is in contact with the peripheral wall of the liquid wick.

5. The liquid metal heat pipe for use in a space microgravity environment according to any one of claims 1 to 3, characterized in that: The metal copper mesh is prepared by sintering irregular copper powder.

6. The liquid metal heat pipe for use in a space microgravity environment according to any one of claims 1 to 3, characterized in that: The liquid metal is a bismuth-based metal.

7. A heat dissipation device, characterized in that: include: A heat collecting plate, a heat dissipating plate, and a liquid metal heat pipe for use in a space microgravity environment as claimed in any one of claims 1 to 6; The evaporation end of the liquid metal heat pipe is connected to the heat collecting plate, and the condensation end of the liquid metal heat pipe is connected to the heat dissipation plate.

8. The heat dissipation device according to claim 7, characterized in that: The central axis of the liquid metal heat pipe is arranged obliquely relative to the plate surface of the heat dissipation plate.

9. The heat dissipation device according to claim 7, characterized in that: The heat dissipation device also includes a circulation channel and an electromagnetic pump; The circulation channel is connected between the evaporation end and the condensation end of the liquid metal heat pipe; the electromagnetic pump is used to drive the liquid metal to flow from the condensation end along the circulation channel to the evaporation end.

10. The heat dissipation device according to claim 9, characterized in that: The heat dissipation device further includes a temperature sensor and a control module; the temperature sensor is electrically connected to the control module, and the control module is electrically connected to the electromagnetic pump; The temperature sensor is disposed on the heat collecting plate and is used to detect temperature information of the heat collecting plate. The control module is used to control the working state of the electromagnetic pump according to the temperature information fed back by the temperature sensor.

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