Satellite surface wave-absorbing skin structure and preparation method thereof

Abstract

The present invention discloses a satellite surface absorbing skin structure, which comprises four layers from top to bottom: a thermal control layer; a wave-transmitting reinforcement layer with a plurality of small holes on its surface; a wave-absorbing honeycomb layer composed of a plurality of regular hexagonal prisms of the same shape and size arranged closely together to form a honeycomb grid with a regular hexagonal cross-section; and a reinforced shielding layer for isolating electromagnetic waves from penetrating both sides of the wave-absorbing skin. The wave-transmitting reinforcement layer is bonded to the top surface of the wave-absorbing honeycomb layer, the reinforced shielding layer is bonded to the bottom surface of the wave-absorbing honeycomb layer, and the thermal control layer is bonded to the upper surface of the wave-transmitting reinforcement layer. While balancing wave absorption and load-bearing properties, the present invention not only achieves broadband radar wave-absorbing properties but also possesses vacuum environment resistance.

Description

Technical Field

[0001] The present invention relates to the field of composite materials, and in particular to a satellite surface wave-absorbing skin structure and a preparation method thereof. Background Art

[0002] Using low-scatter technology to reduce the radar reflection signal of spacecraft can detect and monitor the system's defense capabilities. Regarding the current status of low-scatter spacecraft development, foreign countries developed it earlier and more maturely, such as the United States' "Project Hazy," which has now reached its third generation. The low-scattering characteristics of spacecraft are primarily achieved by reducing the radar cross section (RCS). Common research areas include satellite structure, absorbing, and scattering materials. Conventional spacecraft achieve low scattering through three main approaches: structural design, surface radar absorbing material design (i.e., by applying designed radar absorbing materials to the satellite surface to absorb radar waves), and the application of new concepts and principles. Scattering sources of spacecraft include parabolic antennas, the satellite itself, and solar panels. Therefore, reducing the RCS of a spacecraft generally starts from these scattering sources. The treatment methods include: (1) avoiding the appearance of convex curved surfaces and larger planes, gaps and vertical intersections, edges, corners, and sharp points in the configuration. The transition between contact surfaces should be kept as smooth as possible, and there should be no hanging objects on the outer surface; (2) multi-faceted and fused shape technology to achieve low radar cross-section; (3) body-mounted structures should be selected as much as possible to reduce the RCS value.

[0003] Considering the shape design, the design of low-scattering spacecraft always faces the problem of incident angle. The use of absorbing structures on the satellite surface has become a method to suppress scattering without relying on angle. Traditional absorbing skin materials are mostly made of polymer composite structural materials with strong radar wave absorption capabilities, and some are also coated with absorbing paint on the surface. Satellites are a special type of aircraft, and their weight is a factor directly related to their launch cost. Therefore, when designing low-scattering structures on satellites, the weight and density of the absorbing structure are important technical indicators. Honeycomb structure, as a lightweight absorbing structural material with high strength and load-bearing capacity, has been widely used in the field of absorbing materials. The advantages of low density and strong load-bearing capacity brought by its high degree of hollowing are very obvious in absorbing materials.

[0004] Currently, the design and manufacture of honeycomb absorbing structures primarily focuses on using dielectric honeycombs as templates, then later coating and filling the honeycomb walls with impedance materials, completely impregnating or filling the templates with conductive fibers, and designing multi-layer honeycomb absorbing structures. However, research on honeycomb absorbing materials specifically for space environments is limited. Simple impregnation with absorbing slurries can lead to poor mass loss performance, while the application of magnetic absorbing coatings faces the problem of high density. Filling aramid paper with conductive carbon fibers can lead to high manufacturing costs and unstable mechanical and electrical properties.

[0005] Based on the above problems, the present invention proposes a satellite surface absorbing skin structure and a preparation method thereof. The process and electromagnetic characteristics are designed while considering the quality loss factor. The patterned impedance layer design is applied to the honeycomb forming process to solve the problem of insufficient electromagnetic material filling on the honeycomb template in the subsequent process. The designed material does not reduce the load-bearing characteristics of the honeycomb structure. Summary of the Invention

[0006] The purpose of the present invention is to provide a satellite surface absorbing skin structure and a preparation method thereof, so as to solve the problems and limitations existing in the prior art.

[0007] To achieve the above-mentioned objectives, the present invention provides a satellite surface absorbing skin structure, which comprises four layers from top to bottom: a thermal control layer; a wave-transmitting enhancement layer having a plurality of small holes provided on its surface; a wave-absorbing honeycomb layer composed of a plurality of regular hexagonal prisms of the same shape and size arranged closely together to form a honeycomb grid with a regular hexagonal cross-section; and a reinforced shielding layer for isolating electromagnetic waves from penetrating on both sides of the wave-absorbing skin. The wave-transmitting enhancement layer is bonded to the top surface of the wave-absorbing honeycomb layer, the reinforced shielding layer is bonded to the bottom surface of the wave-absorbing honeycomb layer, and the thermal control layer is bonded to the upper surface of the wave-transmitting enhancement layer.

[0008] Each inner wall of the wave-absorbing honeycomb layer is coated with a conductive film. The conductive film is in the shape of an inward protrusion of a circular ring. Two inward protrusion structures are symmetrically distributed up and down, and the center of the circular ring coincides with the center of the inner wall of the wave-absorbing honeycomb layer.

[0009] The outer diameter of the circular ring of the conductive film is 5 to 7 mm, the inner diameter is 4 to 6 mm, the inner protrusion width is 0.5 to 1 mm, and the inner protrusion width is equal to the ring width of the circular ring; the distance between the two inner protrusions of the conductive film is 0.5 to 1.5 mm, the thickness of the conductive film is 0.02 to 0.04 mm, and the conductivity is 500 to 1200 S / m.

[0010] The inner bottom surface side length of the regular hexagonal prism is 8mm to 12mm, the wall thickness is 0.1mm to 0.3mm, and the side edge length is 8mm to 12mm; the thickness of the wave-transmitting enhancement layer is 0.1mm to 0.2mm; the thickness of the enhanced shielding layer is 0.1mm to 0.2mm; and the thickness of the thermal control layer is 0.1mm to 0.2mm.

[0011] The bottom of the inner wall of the wave-absorbing honeycomb layer is coated with magnetic slurry, and the coating height is 1 to 2 mm and the thickness is 0.1 to 0.3 mm.

[0012] The bottom surface of the enhanced shielding layer is metallized by magnetron sputtering.

[0013] The material of the thermal control layer has a real part relative dielectric constant of 1.8 to 2.5, and an imaginary part relative dielectric constant of 0.01 to 0.05; the wave-transmitting reinforcement layer can be glass fiber or aramid fiber; the reinforced shielding layer can be glass fiber, aramid fiber, or carbon fiber; the material of the conductive film can be indium tin oxide, zinc aluminum oxide, or a mixture of conductive powders such as aluminum powder, carbon powder, silver powder, and copper powder, graphene particles, metal nanowires, phenolic resin, and polyimide resin; the magnetic slurry can be a slurry composed of carbonyl iron, iron silicon, and sendust metal particles and epoxy resin or cyanate ester.

[0014] The present invention also provides a method for preparing a satellite surface absorbing skin, which specifically comprises the following steps:

[0015] S1, preparing a conductive paste and preparing a conductive film by screen printing;

[0016] S2, printing the conductive film obtained in step S1 on paper using screen printing to obtain paper printed with the conductive film;

[0017] S3, laminating, stretching and shaping the paper printed with the conductive film obtained in step S2, soaking it in magnetic slurry, curing it, dipping it in adhesive, and heating it for semi-curing, so that a honeycomb structure is formed to obtain a wave-absorbing honeycomb layer;

[0018] S4. Adhere the thermal control layer, the wave-transmitting reinforcement layer, the wave-absorbing honeycomb layer, and the enhanced shielding layer in sequence from top to bottom to form a wave-absorbing skin structure.

[0019] Specifically, the preparation of the conductive paste specifically includes: mixing a resin with a diluent, and then mixing the diluted resin with conductive particles to obtain a conductive paste. The resin can be a phenolic resin or a polyimide resin, the diluent can be acetone, anhydrous ethanol, or a nitrocellulose lacquer diluent, and the conductive particles can be graphene particles, metal nanowires, or conductive powder.

[0020] Furthermore, the step S4 specifically includes:

[0021] S41. Metallizing the bottom of the enhanced shielding layer by magnetron sputtering. Specifically, a magnetron sputtering chamber is provided with a corresponding metal target material as a raw material, wherein the target material is gold, silver, copper, or an alloy of any two thereof. The enhanced shielding layer is placed in the sputtering chamber. A magnetron cathode target holder is provided at the upper portion of the sputtering chamber. After the sputtering chamber is turned on and sputtering is performed, the metal layer on the surface of the enhanced shielding layer is formed. The sputtering switch is turned off and gas is filled. After stabilization, the enhanced shielding layer is removed.

[0022] S42, laminating and curing the wave-transmitting reinforcement layer, the wave-absorbing honeycomb layer, and the enhanced shielding layer in sequence with an adhesive, and then drilling holes in the wave-transmitting reinforcement layer with a drill bit;

[0023] S43. Use high-temperature resistant silicone to bond the thermal control layer to the surface of the wave-transmitting reinforcement layer to achieve the final satellite surface wave-absorbing skin molding.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The satellite surface absorbing skin of the present invention has a large porosity, broadband absorbing and lightweight properties, and a small material loss ratio.

[0026] 2. The present invention can achieve low scattering and low radiation characteristics of radar and infrared through multi-layer structural design. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the periodic unit structure of the honeycomb wave absorbing structure of the present invention;

[0028] Figure 2 A schematic diagram of the shape and size of the conductive film of the present invention;

[0029] Figure 3 This is a schematic diagram of the dimensions of the honeycomb sandwich layer of the present invention;

[0030] Figure 4 is the reflectivity curve of the wave absorbing structure of the present invention;

[0031] Figure 5 This is a manufacturing flow chart of the wave-absorbing skin composite material of the present invention. DETAILED DESCRIPTION

[0032] The technical content, structural features, achieved objectives and effects of the present invention are described in detail below with reference to preferred embodiments in conjunction with the accompanying drawings.

[0033] It should be noted that the drawings are in a very simplified form and use non-precise proportions. They are only used to conveniently and clearly assist in explaining the embodiments of the present invention, and are not used to limit the conditions for the implementation of the present invention. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed in the present invention without affecting the efficacy and purpose that can be achieved by the present invention.

[0034] It should be noted that, in the present invention, relational terms such as first and second, etc. are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus comprising a series of elements includes not only the elements explicitly listed, but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0035] The present invention proposes a satellite surface absorbing skin structure, such as Figure 1 As shown, the absorbing skin includes a four-layer structure from top to bottom: the first layer is a thermal control layer 1, which is used to prevent the surface temperature of the absorbing skin from being too high due to radiation such as ultraviolet rays; the second layer is a wave-transmitting reinforcement layer 2, which mainly serves as a structural reinforcement layer of the absorbing skin structure; the third layer is an absorbing honeycomb layer 3, which is used to achieve the characteristics of light weight and high-intensity absorption of electromagnetic waves; the fourth layer, that is, the bottom layer, is an enhanced shielding layer 4, which serves as a structural reinforcement component and is used to isolate the electromagnetic waves from penetrating on both sides of the absorbing skin.

[0036] Specifically, if Figure 3 As shown, the absorbing honeycomb layer 3 is composed of a plurality of regular hexagonal prisms of the same shape and size arranged closely together, formed by folding and gluing paper to form a honeycomb grid with a regular hexagonal cross-section. The side length of the inner bottom surface of each regular hexagonal prism is h, which ranges from 8 mm to 12 mm. The wall thickness of each regular hexagonal prism is t, which ranges from 0.1 mm to 0.3 mm. The height of the absorbing honeycomb layer 3, that is, the side edge length of each regular hexagonal prism, is H, which ranges from 8 mm to 12 mm, and H is usually greater than or equal to h.

[0037] The wave-transmitting reinforcement layer 2 is bonded to the top surface of the wave-absorbing honeycomb layer 3 by an adhesive, and a plurality of small holes are provided on the wave-transmitting reinforcement layer 2. On the one hand, electromagnetic waves can pass through the wave-transmitting reinforcement layer 2 into the wave-absorbing honeycomb layer 3, and on the other hand, the wave-absorbing skin is easily exhausted after entering a vacuum; the thickness of the wave-transmitting reinforcement layer 2 is t1, and the range of t1 is 0.1mm to 0.2mm; the enhanced shielding layer 4 is bonded to the bottom surface of the wave-absorbing honeycomb layer 3 by an adhesive, and the bottom surface of the enhanced shielding layer 4 is metallized by magnetron sputtering, so that the wave-absorbing skin has excellent shielding performance; the thickness of the enhanced shielding layer 4 is t2, and the range of t2 is 0.1mm to 0.2mm; the thermal control layer 1 is bonded to the upper surface of the wave-transmitting reinforcement layer 2 by an adhesive, and the thickness of the thermal control layer 1 is t3, and the range of t3 is 0.1mm to 0.2mm.

[0038] Furthermore, each inner wall of the wave-absorbing honeycomb layer 3, that is, the inner side wall of each regular hexagonal prism, is coated with a conductive film 5, such as Figure 2 As shown, the conductive film 5 is in the shape of an annular inward protrusion (or an embedded split resonant ring). The inward protrusion structure is symmetrically distributed vertically, and the center of the annular ring coincides with the center of the inner wall of the absorbing honeycomb layer 3. The outer diameter of the annular ring of the conductive film 5 is R, which ranges from 5 to 7 mm, the inner diameter is r, which ranges from 4 to 6 mm, the width of the inward protrusion is w, which ranges from 0.5 to 1 mm, and w = Rr (i.e., the width of the inward protrusion is equal to the width of the annular ring). The distance between the two inward protrusions, i.e., the opening width, is g, which ranges from 0.5 to 1.5 mm. The thickness of the conductive film 5 is d, which ranges from 0.02 to 0.04 mm. The conductivity of the conductive film 5 is 500 to 1200 S / m.

[0039] Furthermore, the bottom of the inner wall of each regular hexagonal prism of the absorbing honeycomb layer 3 is coated with a magnetic slurry 6. The magnetic loss of the magnetic slurry 6 combined with the electrical loss of the absorbing honeycomb layer 3 helps to improve the loss of electromagnetic waves of the absorbing skin structure, further improving its absorbing ability. The height of the bottom of the inner wall coated with the magnetic slurry 6 is h1, and the range of h1 is 1 to 2 mm. The thickness of the coated magnetic slurry 6 is t4, and the range of t4 is 0.1 to 0.3 mm.

[0040] Preferably, the adhesive may be phenolic resin or cyanate ester.

[0041] Preferably, the wave-absorbing honeycomb layer 3 can be made of folded and bonded aramid paper.

[0042] Preferably, the material of the thermal control layer 1 has a real part of a relative dielectric constant of 1.8 to 2.5, and an imaginary part of a dielectric constant of 0.01 to 0.05. The thermal control layer 1 may adopt a conductive polyimide aluminum-plated secondary surface mirror flexible thermal control film, which has a high reflectivity to the solar spectrum and can reflect most of the solar radiation energy, thereby achieving the thermal insulation effect of the thermal control layer 1.

[0043] Preferably, the wave-transmitting reinforcement layer 2 may be glass fiber or aramid fiber.

[0044] Preferably, the reinforced shielding layer 4 may be glass fiber, aramid fiber, or carbon fiber.

[0045] Preferably, the magnetic slurry 6 may be a slurry composed of metal particles such as carbonyl iron, iron silicon, and sendust, and epoxy resin or cyanate ester.

[0046] Preferably, the conductive film 5 may be made of indium tin oxide, zinc aluminum oxide, or a mixture of conductive powders such as aluminum powder, carbon powder, silver powder, copper powder, graphene particles, metal nanowires, phenolic resin, polyimide resin, etc.

[0047] Preferably, the metal used for magnetron sputtering may be gold, silver, copper, and alloys thereof.

[0048] In this preferred embodiment, in the wave-absorbing honeycomb layer 3, h is preferably 8 mm, t is 0.2 mm, and H is 10 mm; in the wave-transmitting enhancement layer 2, t1 is preferably 0.2 mm; in the enhanced shielding layer 4, t2 is preferably 0.2 mm; in the thermal control layer 1, t3 is preferably 0.2 mm, the real part of the relative dielectric constant of the material is 2, and the imaginary part of the dielectric constant is 0.01; in the conductive film 5, R is preferably 7 mm, r is 5 mm, w is 1 mm, g is 1 mm, d is 0.04 mm, and the conductivity is 1200 S / m; in the magnetic slurry 6, t4 is preferably 0.3 mm.

[0049] The designed absorbing skin structure is imported into the CST software platform, and the reflectivity simulation is performed to analyze the reflectivity of the material under vertical and horizontal polarization. Figure 4 As shown, the absorbing skin structure exhibits excellent absorption performance between 8 and 18 GHz. Within the 8.73 to 18 GHz range, the reflectivity is below -10 dB, indicating that the absorbing skin structure can absorb over 90% of electromagnetic waves. Furthermore, the absorbing performance curve of the absorbing skin structure decreases with increasing frequency, indicating that even lower reflectivity is achieved above 18 GHz.

[0050] On the other hand, the present invention also proposes a method for preparing a satellite surface absorbing skin structure, such as Figure 5 As shown, the specific steps include:

[0051] S1, preparing a conductive film 5, comprising:

[0052] S11. Preparing a conductive paste, specifically: first, mixing a resin with a diluent, which may be acetone, anhydrous ethanol, lacquer thinner, etc., then mixing the diluted resin with conductive particles to obtain a conductive paste, wherein the weight ratio of the conductive particles to the resin is adjusted according to the desired conductivity;

[0053] S12, screen printing, using the principle that the conductive paste is permeable to the patterned portion of the screen and impermeable to the non-patterned portion of the screen, to obtain a conductive film, specifically comprising:

[0054] S121, cutting the paper into the required size;

[0055] S122, fixing the screen frame of the screen on the screen printing table and leveling it, fixing the paper on the printing table, aligning the screen with the circular protruding pattern and the paper, and adjusting the distance between the screen and the paper;

[0056] S123, pouring the conductive paste obtained in step S11 onto the left side of the screen, so that the conductive paste is squeezed from the screen with the circular inner protrusion pattern onto the paper;

[0057] S124, remove the paper and let it stand for one minute to allow the conductive slurry to level, thereby obtaining a conductive film;

[0058] S125. Heat and dry the conductive film in an oven at a temperature of 80° C. to 120° C. for 5 to 10 minutes.

[0059] S2. Print the conductive film obtained in step S1 on paper by screen printing, and then glue and cut the paper.

[0060] S3, forming the wave-absorbing honeycomb layer structure, specifically including:

[0061] S31, placing the paper printed with the conductive film obtained in step S2 into a honeycomb machine for lamination, stretching and shaping to obtain a wave-absorbing honeycomb layer;

[0062] S32, soaking the magnetic slurry and curing: placing the bottom of the absorbing honeycomb layer in a magnetic slurry tank with a depth of 1 to 2 mm, soaking it multiple times to ensure that the thickness of the soaked magnetic slurry reaches 0.1 to 0.3 mm, and then heating it to achieve curing of the magnetic slurry;

[0063] S33, adhesive dipping: Dip the absorbing honeycomb layer into the glue tank of the dipping machine. During the dipping process, the axial direction of the honeycomb cells should be kept perpendicular to the horizontal plane. The dipping liquid is generally thermosetting phenolic resin.

[0064] S34, heating semi-solidification: drying treatment to make the impregnation liquid reach a semi-solidified state.

[0065] S4, wave-absorbing skin structure forming, specifically including:

[0066] S41. Metallizing the bottom of the enhanced shielding layer 4 by magnetron sputtering. Specifically, the magnetron sputtering chamber uses a corresponding metal target material as a raw material. The target material can be gold, silver, copper, and alloys thereof. The enhanced shielding layer 4 is placed in the sputtering chamber. A magnetron cathode target holder is provided on the upper part of the sputtering chamber. An observation window is provided on the front of the sputtering chamber to observe the sputtering state of the sample during the sputtering process. After the sputtering is started and the surface metal layer is formed, the sputtering switch is turned off and gas is filled. After the system stabilizes, the sample is removed.

[0067] S42, laminating and curing the wave-transmitting reinforcement layer 2, the wave-absorbing honeycomb layer 3, and the reinforced shielding layer 4 to achieve integral formation of the wave-absorbing skin structure, and then drilling holes in the wave-transmitting reinforcement layer 2 using a drill bit with a diameter of 1 mm to 2 mm to facilitate exhaust after the skin enters a vacuum;

[0068] S43. Use high-temperature resistant silicone to bond the thermal control layer 1 to the surface of the wave-transmitting reinforcement layer 2 to achieve the final satellite wave-absorbing skin molding.

[0069] In summary, compared with the existing technology, the satellite surface absorbing skin structure and its preparation method provided by the present invention can not only achieve broadband radar absorbing characteristics on the basis of taking into account both absorbing and bearing, but also have the function of resisting vacuum environment.

[0070] Although the present invention has been described in detail through the above preferred embodiments, it should be understood that the above description is not intended to limit the present invention. After reading the above description, various modifications and substitutions of the present invention will become apparent to those skilled in the art. Therefore, the scope of protection of the present invention should be defined by the appended claims.

Claims

1. A satellite surface absorbing skin structure, characterized in that: The wave-absorbing skin structure comprises four layers from top to bottom: Thermal control layer; The wave-transmitting enhancement layer has a plurality of small holes on its surface; The wave-absorbing honeycomb layer is composed of multiple regular hexagonal prisms of the same shape and size arranged closely together to form a honeycomb grid with a regular hexagonal cross section. An enhanced shielding layer for isolating electromagnetic waves from penetrating both sides of the absorbing skin; The wave-transmitting reinforcement layer is bonded to the top surface of the wave-absorbing honeycomb layer, the enhanced shielding layer is bonded to the bottom surface of the wave-absorbing honeycomb layer, and the thermal control layer is bonded to the upper surface of the wave-transmitting reinforcement layer; Each inner wall of the absorbing honeycomb layer is coated with a conductive film, and the conductive film is in the shape of a circular inward protrusion, with two inward protrusion structures symmetrically distributed up and down, and the center of the circular ring coincides with the center of the inner wall of the absorbing honeycomb layer; the bottom of the inner wall of the absorbing honeycomb layer is coated with a magnetic slurry, and the coating height is 1 to 2 mm; The outer diameter of the circular ring of the conductive film is 5 to 7 mm, the inner diameter is 4 to 6 mm, the inner protrusion width is 0.5 to 1 mm, and the inner protrusion width is equal to the ring width of the circular ring; the distance between the two inner protrusions of the conductive film is 0.5 to 1.5 mm, the thickness of the conductive film is 0.02 to 0.04 mm, and the conductivity is 500 to 1200 S / m; The bottom surface of the enhanced shielding layer is metallized by magnetron sputtering.

2. The satellite surface absorbing skin structure according to claim 1, wherein: The inner bottom surface side length of the regular hexagonal prism is 8mm to 12mm, the wall thickness is 0.1mm to 0.3mm, and the side edge length is 8mm to 12mm; the thickness of the wave-transmitting enhancement layer is 0.1mm to 0.2mm; the thickness of the enhanced shielding layer is 0.1mm to 0.2mm; and the thickness of the thermal control layer is 0.1mm to 0.2mm.

3. The satellite surface absorbing skin structure according to claim 1, wherein: The thickness of the magnetic slurry coating is 0.1 to 0.3 mm.

4. The satellite surface absorbing skin structure according to claim 3, wherein: The material of the thermal control layer has a real part of a relative dielectric constant of 1.8 to 2.5 and an imaginary part of a dielectric constant of 0.01 to 0.05; The wave-transmitting reinforcement layer is made of glass fiber or aramid fiber; The reinforced shielding layer is glass fiber, aramid fiber or carbon fiber; The conductive film is made of indium tin oxide or zinc aluminum oxide, or a mixture of conductive particles and resin, wherein the conductive particles are aluminum powder, carbon powder, silver powder, copper powder or metal nanowires; and the resin is phenolic resin or polyimide; The magnetic slurry is a slurry composed of metal particles and epoxy resin or cyanate ester, and the metal particles are carbonyl iron, iron silicon or sendust.

5. A method for preparing a satellite surface absorbing skin, characterized in that: The preparation of the satellite surface absorbing skin structure according to any one of claims 1 to 4 specifically comprises the following steps: S1, preparing a conductive paste and preparing a conductive film by screen printing; S2, printing the conductive film obtained in step S1 on paper using screen printing to obtain paper printed with the conductive film; S3, laminating, stretching and shaping the paper printed with the conductive film obtained in step S2, soaking it in magnetic slurry, curing it, dipping it in adhesive, and heating it for semi-curing, so that a honeycomb structure is formed to obtain a wave-absorbing honeycomb layer; S4. Adhere the thermal control layer, the wave-transmitting reinforcement layer, the wave-absorbing honeycomb layer, and the enhanced shielding layer in sequence from top to bottom to form a wave-absorbing skin structure.

6. The method for preparing a satellite surface absorbing skin according to claim 5, wherein: The preparation of the conductive paste specifically includes: The resin is mixed with a diluent, and then the diluted resin is mixed with conductive particles to obtain a conductive paste. The resin is a phenolic resin or a polyimide resin, the diluent is acetone, anhydrous ethanol or nitrocellulose lacquer diluent, and the conductive particles are metal nanowires or conductive powders.

7. The method for preparing a satellite surface absorbing skin according to claim 5, wherein: The step S4 specifically includes: S41. Metallizing the bottom of the enhanced shielding layer by magnetron sputtering. Specifically, a magnetron sputtering chamber is provided with a corresponding metal target material as a raw material, wherein the target material is gold, silver, copper, or an alloy of any two thereof. The enhanced shielding layer is placed in the sputtering chamber. A magnetron cathode target holder is provided at the upper portion of the sputtering chamber. After the sputtering chamber is turned on and sputtering is performed, the metal layer on the surface of the enhanced shielding layer is formed. The sputtering switch is turned off and gas is filled. After stabilization, the enhanced shielding layer is removed. S42, laminating and curing the wave-transmitting reinforcement layer, the wave-absorbing honeycomb layer, and the enhanced shielding layer in sequence with an adhesive, and then drilling holes in the wave-transmitting reinforcement layer with a drill bit; S43. Use high-temperature resistant silicone to bond the thermal control layer to the surface of the wave-transmitting reinforcement layer to achieve the final satellite surface wave-absorbing skin molding.

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