High-density heat flux heat expansion-heat equalization component for satellite and its manufacturing method

Abstract

The present invention provides a high-density heat flux heat expansion and equalization component for satellites and a manufacturing method thereof, including a component body, wherein the component body includes a thin-walled cavity, a capillary suction structure, a high-permeability micro-groove bearing column, and a working fluid filling tube, wherein the capillary suction structure array is arranged on the inner surfaces of the upper and lower walls of the thin-walled cavity; the high-permeability micro-groove bearing column array is arranged in the thin-walled cavity to support the upper and lower walls of the thin-walled cavity; the working fluid filling tube is arranged on the side wall of the component body, and is used to fill the thin-walled cavity with working fluid. The present invention is manufactured in an integrated manner using a laser selective melting additive manufacturing forming process. The high-density heat flux heat expansion component for satellites designed by the present invention replaces the original heat pipes on the satellite as a rapid heat expansion component for satellite point-shaped high heat flux density devices, converts the one-dimensional heat transfer mode of the heat pipe into a three-dimensional rapid heat expansion mode, strengthens the heat expansion and equalization capacity of the thermal control element, and improves the temperature control effect of the high heat flux density device.

Description

Technical Field

[0001] The present invention relates to the field of mechanical design and manufacturing technology, and in particular, to a high-density heat flux heat expansion-heat equalizing component for satellites and a manufacturing method thereof, and in particular to a high-density heat flux heat expansion-heat equalizing component for satellites oriented to additive manufacturing and a manufacturing method thereof. Background Art

[0002] Traditional satellite conventional heat flux devices use a technical method of sticking a metal heat expansion block between the device and the mounting plate, and burying a heat pipe in the corresponding position of the structural mounting plate to expand and equalize heat. This technical method has the following two disadvantages. On the one hand, the thermal control component is heavy. On the other hand, the thermal conductivity of the aluminum alloy heat expansion block is limited, and the heat pipe can only conduct heat in one dimension along the axial direction, so it can only meet the heat dissipation needs of conventional heat flux devices. The new generation of satellites uses a large number of high heat flux density devices, resulting in continuous generation of heat in small local areas. The traditional "heat expansion block + heat pipe" temperature control method has a heat dissipation rate in a small area that is much lower than the heat source heat generation rate. Heat accumulates in the local area, causing the temperature of the area to rise sharply in a short period of time, thereby inducing device failure.

[0003] Flat steam chamber technology is a type of heat dissipation technology developed based on vacuum chamber heat dissipation technology. It can achieve rapid diffusion of high-density heat flow, effectively reduce local heat flux density, and transform the high heat flux density temperature control problem into a conventional temperature control problem. Flat steam chamber is a three-dimensional heat conductor with the advantages of strong thermal conductivity, excellent temperature uniformity, high limit heat flux density, and high operating stability. It can achieve rapid diffusion of high-density heat flow and has been widely used and paid attention to in the heat dissipation of concentrated heat sources with high heat flux density such as light-emitting diodes and ultra-high-performance CPUs in the civilian industry. The capillary structure inside the flat steam chamber is the key to achieving phase change heat transfer, which can generally be divided into three types: copper powder sintering type, groove type, and wire mesh type. The copper powder sintering type and wire mesh type capillary core structure have a large capillary pressure, but the permeability is relatively small, and a large contact thermal resistance is formed between the porous sintered liquid-absorbing core layer and the wall shell, which also has a great influence on the heat transfer capacity of the flat steam chamber. The grooved capillary structure can be formed by micro-embossing on the cavity wall, and has the advantages of high permeability, thin wall, light weight, small contact thermal resistance, fast thermal response, and the wick structure is not easy to damage. However, due to the limitations of traditional micro-embossing manufacturing methods, the capillary structure has a small depth (less than 200 microns), a small aspect ratio (less than 1), and a limited structural form, resulting in a small capillary pressure and a limited ultimate heat flux density. In addition, the existing copper powder sintering, groove, and wire mesh steam chambers are all made of multi-component multi-point welding of cavity cover plates, load-bearing structures, etc., with high leakage risks and low reliability, which cannot meet the high reliability requirements of satellites.

[0004] In view of the shortcomings of traditional methods, the present invention innovatively designs a high-density heat flux expansion and heat equalization component for satellites for additive manufacturing. It adopts innovative design configurations such as a large aspect ratio truncated cone configuration gradient capillary suction structure array and a single-leaf hyperbolic configuration high permeability microgroove bearing column array to simultaneously improve the capillary pressure and permeability, and performs integrated laser selective melting additive manufacturing of the cavity, capillary suction structure array, and bearing column array. It has the advantages of high ultimate heat flux density, no leakage risk caused by multi-point welding, and high reliability, which improves the temperature control effect of high heat flux density devices for satellites. Summary of the invention

[0005] In view of the defects in the prior art, the object of the present invention is to provide a high-density heat flux heat expansion-heat equalization component for satellites and a manufacturing method thereof.

[0006] The high-density heat flux expansion and heat equalization component for satellites provided by the present invention comprises a component body, wherein the component body comprises a thin-wall cavity, a capillary suction structure, a high-permeability micro-groove bearing column, and a working fluid filling pipe, wherein:

[0007] The capillary suction structure array is arranged on the inner surfaces of the upper and lower walls of the thin-walled cavity;

[0008] An array of high-permeability micro-groove bearing columns is arranged in the thin-wall cavity to support the upper and lower walls of the thin-wall cavity;

[0009] The working medium filling pipe is arranged on the side wall of the component body and is used for filling the working medium into the thin-wall cavity.

[0010] Preferably, the component body is made of aluminum alloy material and is integrally manufactured using a laser selective melting forming process.

[0011] Preferably, the wall thickness of the thin-wall cavity is 1 mm-1.2 mm.

[0012] Preferably, the inner cavity height of the thin-walled cavity is 2mm-3mm.

[0013] Preferably, the capillary suction structure adopts a truncated cone configuration capillary suction structure; the truncated cone configuration capillary suction structure array is arranged on the inner surface of the upper and lower walls of the thin-walled cavity, along the rectangular array, and the array spacing is 0.1 mm.

[0014] Preferably, the frustum-cone capillary suction structure adopts a gradient layout design, wherein the height of the frustum-cone microstructure unit in the non-high heat flux heat source area is 0.7mm-0.8mm, the height of the frustum-cone microstructure unit in the point-shaped high heat flux heat source area is 0.5mm-0.6mm, and the angle between the frustum generatrix and the thin-walled inner surface of the cavity is 60°-65°.

[0015] Preferably, the high seepage microgroove bearing column adopts a single-leaf hyperboloid high seepage microgroove bearing column, and the surface equation corresponding to the cross section of the single-leaf hyperboloid high seepage microgroove bearing column along the central axis satisfies: Wherein: x, y, z represent coordinate points of a rectangular three-dimensional coordinate system, z represents the axis corresponding to the central axis of the single-leaf hyperboloid configuration high-permeability microgroove bearing column; t2 is the diameter of the cross-section of the single-leaf hyperboloid configuration high-permeability microgroove bearing column divided into two equal parts along the height direction; t3 is the diameter of the upper and lower end surfaces of the single-leaf hyperboloid configuration high-permeability microgroove bearing column; the design range of the diameter t2 of the cross-section of the single-leaf hyperboloid configuration high-permeability microgroove bearing column divided into two equal parts along the height direction is 4mm to 6mm, and the design range of the asymptote angle β of the single-leaf hyperboloid is 25° to 35°; the bearing columns are arranged along a rectangular array, and the array spacing and number are determined by finite element simulation.

[0016] Preferably, the high permeability microgrooves of the high permeability microgroove bearing column are axially connected to the high permeability microgroove bearing column and are arrayed along the circumferential direction of the high permeability microgroove bearing column with an array angle of 60°; the cross-section of the high permeability microgroove is rectangular with a depth of 0.5-0.7mm and a depth-to-width ratio of 0.8.

[0017] Preferably, the working fluid filling tube has an outer diameter of 5 mm and an inner diameter of 3 mm, and the inner diameter also serves as an additive powder cleaning hole.

[0018] Preferably, the thin-walled cavity is filled with liquid ammonia as a working medium, and the filling amount of the liquid ammonia as a working medium is 10%-12% of the volume of the thin-walled cavity. After filling, the working medium filling pipe is cut off and sealed with cold welding pliers.

[0019] According to the present invention, a method for manufacturing the high-density heat flux heat expansion-heat equalization component for satellites described above comprises the following steps:

[0020] Step S1: Considering the constraints of the selective laser melting laser additive manufacturing process on the overhang angle of the structure, a high-density heat flux expansion-heat equalization component for satellites for additive manufacturing is designed, including a thin-walled cavity, a capillary suction structure, a high-permeability micro-groove bearing column, and a working fluid filling pipe. The design range of the wall thickness of the thin-walled cavity is 1mm to 1.2mm; the design range of the inner cavity height of the thin-walled cavity is 2mm to 3mm, and the frustum-conical capillary suction structure array is arranged on the inner surface of the upper and lower walls of the thin-walled cavity, along the rectangular Array; The truncated cone configuration capillary suction microstructure adopts a gradient layout design, in which the height design range of the array truncated cone microstructure unit in the non-high heat flux heat source area is 0.7mm~0.8mm, the height design range of the array truncated cone microstructure unit in the point high heat flux heat source area is 0.5mm~0.6mm, and the angle design range between the truncated cone generatrix and the inner surface of the cavity thin wall is 30°~35°; the high seepage microgroove bearing column array adopts a single-leaf hyperbolic configuration, and the surface equation satisfies:

[0021]

[0022] The design range of the diameter t2 of the cross section of the load-bearing column bisected along the height direction is 4mm-6mm, and the design range of the angle β of the asymptote of the single-leaf hyperboloid is 25°-35°; the load-bearing column is arranged along a rectangular array, and the array spacing and number are determined by finite element simulation; the high-permeability microgrooves are axially connected to the load-bearing column and arranged along the circumferential direction of the load-bearing column, and the array angle is 60°; the microgroove cross-section is rectangular, the depth is 0.5-0.7mm, and the aspect ratio is 0.8; the working fluid filling pipe is located on the side wall of the component, and the working fluid filling pipe has an outer diameter of 5mm and an inner diameter of 3mm, and the inner diameter is also used as an additive powder cleaning hole;

[0023] Step S2: performing a laser selective melting forming process constraint analysis on the designed satellite high-density heat flux heat expansion-heat equalization component for additive manufacturing, and adjusting the structural parameters of each characteristic unit according to the forming direction of the satellite high-density heat flux heat expansion-heat equalization component to meet the free forming conditions;

[0024] Step S3: using appropriate laser selective melting forming process parameters to complete the manufacture of a high-density heat flux heat expansion and heat equalization component for satellites for additive manufacturing;

[0025] Step S4: filling the component cavity with liquid ammonia as the working medium through the working medium filling pipe, the filling amount being 10%-12% of the volume of the heat pipe capillary cavity; after filling, the working medium filling pipe is cut off and sealed with cold welding pliers;

[0026] Step S5: Install high heat flux and conventional heat flux components on the high-density heat flux heat expansion and heat equalization component.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. The present invention proposes a high-density heat flux expansion and heat equalization component for satellites oriented to additive manufacturing. It adopts innovative design configurations such as a large aspect ratio truncated cone configuration gradient capillary suction structure array and a single-leaf hyperbolic configuration high permeability microgroove bearing column array to simultaneously improve capillary pressure and permeability, and performs integrated laser selective melting additive manufacturing of the cavity, capillary suction structure array, and bearing column array. It has the advantages of high ultimate heat flux density, no leakage risk caused by multi-point welding, and high reliability. It solves the problem that the original conventional thermal control means of satellites have one-way heat transfer and cannot meet the efficient heat expansion and heat equalization requirements of the new generation of high heat flux density devices for satellites, and effectively improves the temperature control effect of high heat flux devices.

[0029] 2. The high-density heat flux heat expansion and heat equalization component for satellites proposed in the present invention is manufactured in an integrated manner using the selective laser melting laser additive manufacturing process, avoiding the disadvantages of the existing three types of steam chamber heat expansion components, namely copper powder sintering, groove type, and wire mesh type, which use cavity cover plates, load-bearing structures and other multi-component multi-point welding, high leakage risk, low reliability, and inability to meet the high reliability requirements of satellites.

[0030] 3. The present invention has broad application prospects in the aerospace field. The present invention can also be extended to other industries with similar needs, with considerable economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0032] Figure 1 It is a schematic diagram of the overall structure of a high-density heat flux heat expansion-heat equalization component for satellites for additive manufacturing in the present invention under working conditions;

[0033] Figure 2 The schematic cross-sectional view taken along the AA direction is of a high-density heat flux heat expansion and heat equalization component for satellites oriented to additive manufacturing according to the present invention.

[0034] Figure 3 The schematic cross-sectional view along the BB direction is a schematic cross-sectional view of a high-density heat flux heat expansion-heat equalization component for satellites oriented to additive manufacturing according to the present invention.

[0035] Figure 4 It is a three-dimensional schematic diagram of a high-permeability load-bearing column of a high-density heat flux heat expansion and heat equalization component for satellites oriented to additive manufacturing according to the present invention.

[0036] In the figure: 1- high-density heat flux expansion-heat equalization component; 2- working fluid filling tube; 3- thin-walled cavity; 4- gradient capillary suction structure array; 5- high permeability micro-groove bearing column array. DETAILED DESCRIPTION

[0037] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0038] like Figures 1 to 4 As shown, a high-density heat flux expansion and heat equalization component for satellites for additive manufacturing provided according to the present invention includes a thin-wall cavity, an array of frustum-shaped capillary suction gradient microstructures, an array of high-permeability microgroove bearing columns, and a working fluid filling pipe, which is manufactured in an integrated manner using a laser selective melting forming process.

[0039] Furthermore, the design range of the wall thickness t1 of the thin-walled cavity is 1 mm to 1.2 mm. The design range of the inner cavity height of the thin-walled cavity is 2 mm to 3 mm. The thin-walled cavity is a closed cavity, which is sealed after the tooling is filled through the working medium filling pipe.

[0040] Furthermore, the array of the frustum-cone capillary suction microstructures is arranged on the inner surfaces of the upper and lower walls of the thin-walled cavity. The array of the frustum-cone capillary suction microstructures adopts a gradient layout design, wherein the height design range of the array frustum-cone microstructure units in the non-high heat flux heat source area is 0.7mm-0.8mm, the height design range of the array frustum-cone microstructure units in the point-shaped high heat flux heat source area is 0.5mm-0.6mm, and the angle design range between the frustum generatrix and the thin-walled inner surface of the cavity is 30°-35°. Figure 3 As shown, h1 represents the height of the arrayed truncated cone microstructure unit in the non-high heat flux heat source area; h2 represents the height of the arrayed truncated cone microstructure unit in the point-like high heat flux heat source area; α represents the angle between the truncated cone generatrix and the inner surface of the cavity thin wall.

[0041] Furthermore, the array high-permeability micro-groove bearing column adopts a single-leaf hyperboloid configuration, and the surface equation satisfies:

[0042]

[0043] Among them, t2 represents the diameter of the cross-section bisected by the load-bearing column along the height direction; t3 represents the diameter of the upper and lower end faces of the load-bearing column; s represents the depth of the high-seepage microgroove; L represents the cavity height / load-bearing column height; β represents the angle between the asymptotes of the single-leaf hyperboloid; the design range of the diameter t2 of the cross-section bisected by the load-bearing column along the height direction is 4mm~6mm, and the design range of the angle between the asymptotes of the single-leaf hyperboloid β is 25°~35°; the load-bearing columns are arranged along a rectangular array, and the array spacing and number are determined by finite element simulation, and the determination principle is as follows: under the action of the maximum steam pressure in the cavity and the upper surface load, the maximum strain of the component is not more than 100Mpa, and the maximum deformation does not exceed 0.01mm.

[0044] Furthermore, the high permeability microgrooves are axially penetrated along the load-bearing column and are arrayed along the circumferential direction of the load-bearing column, with an array angle of 60°; the microgrooves are rectangular in cross section, with a depth of 0.5-0.7 mm and a depth-to-width ratio of 0.8.

[0045] Furthermore, the working fluid filling pipe is located on the side wall of the component, and the working fluid filling pipe has an outer diameter of 5 mm and an inner diameter of 3 mm, and the inner diameter is also used as an additive powder cleaning hole. The capillary cavity is filled with liquid ammonia working fluid, and the filling amount is 10%-12% of the volume of the heat pipe capillary cavity. After filling, the working fluid filling pipe is cut off and sealed with cold welding pliers.

[0046] like Figure 1-4 As shown, the high-density heat flux heat expansion and heat equalization component for satellites for additive manufacturing provided by the present invention is manufactured in an integrated manner using a laser selective melting forming process, and the specific implementation steps are as follows:

[0047] Step 1: Complete the design of a high-density heat flux expansion and heat equalization component for satellites for additive manufacturing. The satellite high-density heat flux device expansion component includes a thin-walled cavity, a large aspect ratio truncated cone gradient capillary suction structure array, a single-leaf hyperboloid high-permeability micro-groove bearing column array, a working fluid filling pipe and other structural features. The design range of the wall thickness of the thin-walled cavity is 1mm to 1.2mm; the design range of the inner cavity height of the thin-walled cavity is 2mm to 3mm. The truncated cone capillary suction structure array is arranged on the inner surface of the upper and lower walls of the thin-walled cavity, along the rectangular array. The arrayed truncated cone capillary suction microstructure adopts a gradient layout design, wherein the height design range of the arrayed truncated cone microstructure unit in the non-high heat flux heat source area is 0.7mm-0.8mm, the height design range of the arrayed truncated cone microstructure unit in the point-shaped high heat flux heat source area is 0.5mm-0.6mm, and the angle design range between the truncated cone generatrix and the inner surface of the cavity thin wall is 30°-35°. The arrayed high permeability microgroove bearing column adopts a single-leaf hyperbolic configuration, and the surface equation satisfies:

[0048]

[0049] The design range of the diameter t2 of the bisecting section of the load-bearing column along the height direction is 4mm~6mm, and the design range of the angle β of the asymptote of the single-leaf hyperboloid is 25°~35°; the load-bearing column is along a rectangular array, and the array spacing and number are determined by finite element simulation. The determination principle is as follows: under the action of the maximum steam pressure in the cavity and the upper surface load, the maximum strain of the component is not more than 100Mpa, and the maximum deformation does not exceed 0.01mm. The high permeability microgrooves are axially connected along the load-bearing column and arrayed along the circumferential direction of the load-bearing column, with an array angle of 60°; the microgrooves are rectangular in cross section, with a depth of 0.5-0.7mm and a depth-to-width ratio of 0.8. The working fluid filling pipe is located on the side wall of the component, and the working fluid filling pipe has an outer diameter of 5mm and an inner diameter of 3mm. The inner diameter is also used as an additive powder cleaning hole.

[0050] Step 2: Perform laser selective melting forming process constraint analysis on a high-density heat flux heat expansion and heat equalization component designed for satellites for additive manufacturing. According to the forming direction of the high-density heat flux heat expansion and heat equalization component for satellites, adjust the structural parameters of each characteristic unit to meet the free forming conditions.

[0051] Step 3, using appropriate laser selective melting forming process parameters to complete the manufacture of a high-density heat flux heat expansion and heat equalization component for satellites for additive manufacturing.

[0052] Step 4, fill the component cavity with liquid ammonia working medium through the working medium filling pipe, the filling amount is 10%-12% of the volume of the heat pipe capillary cavity, and after filling, use cold welding pliers to cut off and seal the working medium filling pipe.

[0053] Step 5, install high heat flux and conventional heat flux devices on the high-density heat flux heat expansion-heat equalization component.

[0054] The working principle of the present invention is as follows: When the high heat flux device is working, the heat it dissipates is transferred to the evaporation end of the heat expansion and heat equalization component. When the evaporation end is heated, the working fluid is heated and evaporates and reaches the condensation surface through the vacuum cavity of the component, and the non-heated areas of the cavity are all condensation surfaces. The gaseous working fluid releases heat at a lower temperature and condenses into a liquid. The condensed liquid working fluid flows back to the evaporation end under the action of the capillary driving force of the truncated cone configuration gradient capillary suction structure, forming a closed loop. The essence of its heat conduction is the phase change heat transfer of the working fluid, and the temperature is kept unchanged to achieve temperature control of the high heat flux device. Among them, the capillary suction structure in the heat source area has smaller pores, which will provide a higher capillary pressure to drive the liquid to reflux.

[0055] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0056] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A high-density heat flux heat expansion and heat equalization component for satellites, characterized in that: The component body includes a thin-wall cavity, a capillary suction structure, a high-permeability micro-groove bearing column, and a working fluid filling pipe, wherein: The capillary suction structure array is arranged on the inner surfaces of the upper and lower walls of the thin-walled cavity; An array of high-permeability micro-groove bearing columns is arranged in the thin-wall cavity to support the upper and lower walls of the thin-wall cavity; The working medium filling pipe is arranged on the side wall of the component body and is used to fill the working medium into the thin-wall cavity; The capillary suction structure adopts a truncated cone configuration capillary suction structure; The truncated cone capillary suction structure adopts a gradient layout design, wherein the height of the truncated cone microstructure unit in the non-high heat flux heat source area is 0.7mm-0.8mm, the height of the truncated cone microstructure unit in the point-shaped high heat flux heat source area is 0.5mm-0.6mm, and the angle between the truncated cone generatrix and the inner surface of the cavity thin wall is 60°-65°; The high seepage microgroove bearing column adopts a single-leaf hyperboloid high seepage microgroove bearing column, and the surface equation corresponding to the cross section of the single-leaf hyperboloid high seepage microgroove bearing column along the central axis satisfies: Wherein: x, y, z represent coordinate points of a rectangular three-dimensional coordinate system, z represents the axis corresponding to the central axis of the single-leaf hyperboloid configuration high-permeability microgroove bearing column; t2 is the diameter of the cross-section of the single-leaf hyperboloid configuration high-permeability microgroove bearing column divided into two equal parts along the height direction; t3 is the diameter of the upper and lower end surfaces of the single-leaf hyperboloid configuration high-permeability microgroove bearing column; the design range of the diameter t2 of the cross-section of the single-leaf hyperboloid configuration high-permeability microgroove bearing column divided into two equal parts along the height direction is 4mm to 6mm, and the design range of the asymptote angle β of the single-leaf hyperboloid is 25° to 35°; the bearing columns are arranged along a rectangular array, and the array spacing and number are determined by finite element simulation.

2. The high-density heat flux heat expansion and heat equalization component for satellites according to claim 1, characterized in that: The component body is made of aluminum alloy material and is integrally manufactured by laser selective melting forming process.

3. The high-density heat flux heat expansion and heat equalization component for satellite according to claim 1, characterized in that: The wall thickness of the thin-wall cavity is 1 mm-1.2 mm.

4. The high-density heat flux heat expansion and heat equalization component for satellites according to claim 1, characterized in that: The inner cavity height of the thin-wall cavity is 2mm-3mm.

5. The high-density heat flux heat expansion and heat equalization component for satellite according to claim 1, characterized in that: The frustum-cone-shaped capillary suction structure arrays are arranged on the inner surfaces of the upper and lower walls of the thin-walled cavity, along the rectangular array, with an array spacing of 0.1 mm.

6. The high-density heat flux heat expansion and heat equalization component for satellite according to claim 1, characterized in that: The high permeability microgrooves of the high permeability microgroove bearing column are axially connected to the high permeability microgroove bearing column and are arranged in an array along the circumferential direction of the high permeability microgroove bearing column with an array angle of 60°; the cross-section of the high permeability microgroove is rectangular with a depth of 0.5-0.7mm and a depth-to-width ratio of 0.

8.

7. The high-density heat flux heat expansion and heat equalization component for satellite according to claim 1, characterized in that: The working fluid filling tube has an outer diameter of 5 mm and an inner diameter of 3 mm, and the inner diameter is also used as an additive powder cleaning hole.

8. The high-density heat flux heat expansion and heat equalization component for satellites according to claim 1, characterized in that: The thin-wall cavity is filled with liquid ammonia as a working medium, and the filling amount of the liquid ammonia as a working medium is 10%-12% of the volume of the thin-wall cavity. After filling, the working medium filling pipe is cut off and sealed with cold welding pliers.

9. A method for manufacturing a high-density heat flux heat expansion and heat equalization component for satellites according to any one of claims 1 to 8, characterized in that: The steps include: Step S1: Design a high-density heat flux expansion and heat equalization component for satellites for additive manufacturing, including a thin-walled cavity, a capillary suction structure, a high-permeability micro-groove bearing column, and a working fluid filling pipe. The design range of the wall thickness of the thin-walled cavity is 1 mm to 1.2 mm; the design range of the inner cavity height of the thin-walled cavity is 2 mm to 3 mm, and the frustum-conical configuration capillary suction structure array is arranged on the upper and lower wall inner surfaces of the thin-walled cavity, along the rectangular array; the frustum-conical configuration capillary suction microstructure adopts a gradient layout design, wherein the height design range of the array frustum-conical microstructure unit in the non-high heat flux heat source area is 0.7 mm to 0.8 mm, the height design range of the array frustum-conical microstructure unit in the point-shaped high heat flux heat source area is 0.5 mm to 0.6 mm, and the angle design range between the frustum generatrix and the thin wall inner surface of the cavity is 30° to 35°; the high-permeability micro-groove bearing column array adopts a single-leaf hyperbolic configuration, and the surface equation satisfies: The design range of the diameter t2 of the cross section of the load-bearing column bisected along the height direction is 4mm-6mm, and the design range of the angle β of the asymptote of the single-leaf hyperboloid is 25°-35°; the load-bearing column is arranged along a rectangular array, and the array spacing and number are determined by finite element simulation; the high-permeability microgrooves are axially connected to the load-bearing column and arranged along the circumferential direction of the load-bearing column, and the array angle is 60°; the microgroove cross-section is rectangular, the depth is 0.5-0.7mm, and the aspect ratio is 0.8; the working fluid filling pipe is located on the side wall of the component, and the working fluid filling pipe has an outer diameter of 5mm and an inner diameter of 3mm, and the inner diameter is also used as an additive powder cleaning hole; Step S2: performing a laser selective melting forming process constraint analysis on the designed satellite high-density heat flux heat expansion-heat equalization component for additive manufacturing, and adjusting the structural parameters of each characteristic unit according to the forming direction of the satellite high-density heat flux heat expansion-heat equalization component to meet the free forming conditions; Step S3: using laser selective melting forming process parameters to complete the integrated manufacturing of high-density heat flux heat expansion and heat equalization components for satellites for additive manufacturing; Step S4: filling the component cavity with liquid ammonia as the working medium through the working medium filling pipe, the filling amount being 10%-12% of the volume of the heat pipe capillary cavity; after filling, the working medium filling pipe is cut off and sealed with cold welding pliers; Step S5: Install high heat flux and conventional heat flux components on the high-density heat flux heat expansion and heat equalization component.

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