CN116080218A - Satellite surface wave-absorbing skin structure and preparation method thereof - Google Patents

Satellite surface wave-absorbing skin structure and preparation method thereof Download PDF

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Publication number
CN116080218A
CN116080218A CN202211430287.2A CN202211430287A CN116080218A CN 116080218 A CN116080218 A CN 116080218A CN 202211430287 A CN202211430287 A CN 202211430287A CN 116080218 A CN116080218 A CN 116080218A
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wave
layer
absorbing
honeycomb
conductive film
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许勇刚
高伟
王晓冰
张慧媛
米晓林
付鑫
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Shanghai Radio Equipment Research Institute
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Shanghai Radio Equipment Research Institute
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    • B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
    • B32B27/281—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42 comprising polyimides
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
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    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/20—Metallic material, boron or silicon on organic substrates
    • C23C14/205—Metallic material, boron or silicon on organic substrates by cathodic sputtering
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    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/34—Sputtering
    • C23C14/35—Sputtering by application of a magnetic field, e.g. magnetron sputtering
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H05K9/0073—Shielding materials
    • H05K9/0081—Electromagnetic shielding materials, e.g. EMI, RFI shielding
    • H05K9/0088—Electromagnetic shielding materials, e.g. EMI, RFI shielding comprising a plurality of shielding layers; combining different shielding material structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking
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Abstract

The invention discloses a satellite surface wave-absorbing skin structure, which sequentially comprises four layers of structures from top to bottom: a thermal control layer; the surface of the wave-transmitting enhancement layer is provided with a plurality of small holes; the wave-absorbing honeycomb layer is formed by closely arranging a plurality of regular hexagonal prisms with the same shape and size, and honeycomb cells with regular hexagons in cross section are formed; the reinforced shielding layer is used for isolating electromagnetic wave penetration at two sides of the wave-absorbing skin; the wave-transmitting enhancement layer is adhered to the surface of the top layer of the wave-absorbing honeycomb layer, the enhancement shielding layer is adhered to the surface of the bottom layer of the wave-absorbing honeycomb layer, and the thermal control layer is adhered to the upper surface of the wave-transmitting enhancement layer. The invention not only can realize the wave absorbing characteristic of the broadband radar, but also has the function of vacuum-resistant environment on the basis of taking wave absorbing and bearing into consideration.

Description

Satellite surface wave-absorbing skin structure and preparation method thereof
Technical Field
The invention relates to the field of composite materials, in particular to a satellite surface wave-absorbing skin structure and a preparation method thereof.
Background
The ability of the system to resist is detected and monitored using low scattering techniques in reducing radar reflected signals from the spacecraft. With respect to the current state of development of low scattering spacecraft, earlier and mature development abroad, such as the "hazy program" in the united states, has now progressed to the third generation. The low scattering properties of spacecraft are mainly achieved by reducing Radar Cross Section (RCS), and several aspects of general research are satellite structures, wave absorbing and wave scattering materials. Conventional spacecraft achieve low scattering mainly by three approaches: the design of the structure, the design of the surface radar absorbing material (namely, the radar absorbing material is applied to the satellite surface to absorb radar waves), and the things applying some new concepts and new principles. The scattering source of the spacecraft comprises: parabolic antenna, body, solar array. Thus, the means of reducing RCS of a spacecraft, generally starting from these several scattering sources, include: (1) The convex curved surface, larger plane, notch and vertically crossed joint surface, edge angle and sharp point are avoided, smooth transition is kept between the contact surfaces as much as possible, and hanging objects do not appear on the outer surface; (2) The multi-faceted surface and the fused profile technology achieve low radar cross-sectional area; (3) The body-mounted structure is selected as much as possible to reduce the RCS value.
Considering the problem that the appearance design always faces the incident angle in the design of the low-scattering spacecraft, the wave-absorbing structure is adopted for the satellite surface to be a method capable of inhibiting scattering without depending on the angle. The traditional wave-absorbing skin material is a polymer composite structure material with extremely strong wave-absorbing radar wave energy, and part of the polymer composite structure material is also coated with wave-absorbing paint on the surface. Satellites are a special class of aircraft, and the weight is a factor directly related to the transmission cost, so the weight and density of a wave absorbing structure are important technical indexes when low scattering design is performed on the satellites. The honeycomb structure is widely applied to the field of wave-absorbing materials as a high-strength bearing light wave-absorbing structural material, and the advantages of low density and strong bearing capacity caused by high hollowness degree are obvious on the wave-absorbing material.
At present, the design and manufacture of a surrounding honeycomb wave-absorbing structure mainly concentrate on taking a medium honeycomb as a template, coating and filling impedance materials on the surface of a honeycomb wall at the later stage, completely impregnating or filling conductive fibers on the surface of the template, and carrying out multilayer structural design on the honeycomb wave-absorbing structure, but the wave-absorbing honeycomb material for space environment has less research. The problem of poor quality loss performance easily occurs in the simple dipping wave-absorbing slurry, the problem of high density is faced by the coating of the magnetic wave-absorbing coating, and the problems of high manufacturing cost and unstable mechanical and electrical properties are easily caused by filling the conductive carbon fiber in the manufacturing of the aramid paper.
Based on the above problems, the invention provides a satellite surface wave-absorbing skin structure and a preparation method thereof, wherein the technology and electromagnetic characteristics are designed under consideration of quality loss factors, the design of a patterned impedance layer is applied to the honeycomb molding process, the problem of insufficient electromagnetic material filling on a honeycomb template is solved, and the designed material does not reduce the bearing characteristics of the honeycomb structure.
Disclosure of Invention
The invention aims to provide a satellite surface wave-absorbing skin structure and a preparation method thereof, which solve the problems and limitations in the prior art.
In order to achieve the above purpose, the invention provides a satellite surface wave-absorbing skin structure, which comprises four layers of structures from top to bottom: a thermal control layer; the surface of the wave-transmitting enhancement layer is provided with a plurality of small holes; the wave-absorbing honeycomb layer is formed by closely arranging a plurality of regular hexagonal prisms with the same shape and size, and honeycomb cells with regular hexagons in cross section are formed; the reinforced shielding layer is used for isolating electromagnetic wave penetration at two sides of the wave-absorbing skin; the wave-transmitting enhancement layer is adhered to the surface of the top layer of the wave-absorbing honeycomb layer, the enhancement shielding layer is adhered to the surface of the bottom layer of the wave-absorbing honeycomb layer, and the thermal control layer is adhered to the upper surface of the wave-transmitting enhancement layer.
Each inner wall of the wave-absorbing honeycomb layer is coated with a conductive film, the conductive film is in a ring inward protruding shape, the two inward protruding structures are distributed symmetrically up and down, and the center of the ring is coincident with the center of the inner wall of the wave-absorbing honeycomb layer.
The outer diameter of the circular ring of the conductive film is 5-7 mm, the inner diameter of the circular ring is 4-6 mm, the inward protruding width of the circular ring is 0.5-1 mm, and the inward protruding width is equal to the ring width of the circular ring; the distance between two inward protrusions of the conductive film is 0.5-1.5 mm, the thickness of the conductive film is 0.02-0.04 mm, and the conductivity is 500-1200S/m.
The side length of the inner bottom surface of the regular hexagonal prism is 8-12 mm, the wall thickness is 0.1-0.3 mm, and the side edge length is 8-12 mm; the thickness of the wave-transmitting enhancement layer is 0.1 mm-0.2 mm; the thickness of the reinforced shielding layer is 0.1 mm-0.2 mm; the thickness of the thermal control layer is 0.1 mm-0.2 mm.
The bottom of the inner wall of the wave-absorbing honeycomb layer is coated with magnetic slurry, the coating height is 1-2 mm, and the thickness is 0.1-0.3 mm.
And the bottom surface of the enhanced shielding layer is metallized by magnetron sputtering.
The real part of the relative dielectric constant of the material of the thermal control layer is 1.8-2.5, and the imaginary part of the dielectric constant is 0.01-0.05; the wave-transmitting reinforcing layer can be glass fiber and aramid fiber; the reinforced shielding layer can be glass fiber, aramid fiber and carbon fiber; the conductive film can be made of indium tin oxide and zinc aluminum oxide, or can be made of conductive powder such as aluminum powder, carbon powder, silver powder and copper powder, graphene particles, a mixture of metal nanowires, phenolic resin and polyimide resin; the magnetic slurry can be slurry formed by carbonyl iron, iron silicon aluminum metal particles and epoxy resin or cyanate ester.
The invention also provides a preparation method of the satellite surface wave-absorbing skin, which comprises the following steps:
s1, preparing conductive paste, and preparing a conductive film through screen printing;
s2, printing the conductive film obtained in the step S1 on paper by screen printing to obtain paper printed with the conductive film;
s3, carrying out superposition, stretching and shaping, magnetic slurry soaking, curing, adhesive dipping and heating semi-curing treatment on the paper printed with the conductive film obtained in the step S2, so that the honeycomb structure is formed, and a wave-absorbing honeycomb layer is obtained;
and S4, sequentially bonding the thermal control layer, the wave-transmitting enhancement layer, the wave-absorbing honeycomb layer and the enhancement shielding layer from top to bottom to form a wave-absorbing skin structure.
Specifically, the preparation of the conductive paste specifically comprises the following steps: mixing resin with diluent, and mixing diluted resin with conductive particles to obtain conductive slurry, wherein the resin can be phenolic resin and polyimide resin, the diluent can be acetone, absolute ethyl alcohol and nitrolacquer diluent, and the conductive particles can be graphene particles, metal nanowires and conductive powder.
Further, the step S4 specifically includes:
s41, carrying out metallization on the bottom of the enhanced shielding layer by adopting magnetron sputtering, specifically, taking a corresponding metal target material as a raw material in a magnetron sputtering chamber, placing the enhanced shielding layer in the sputtering chamber, setting a magnetron cathode target support at the upper part of the sputtering chamber, starting up to implement sputtering, completing the manufacture of the metal layer on the surface of the enhanced shielding layer, closing a sputtering switch, filling gas, and taking out the enhanced shielding layer after stabilization;
s42, sequentially laminating and curing the wave-transmitting enhancement layer, the wave-absorbing honeycomb layer and the enhanced shielding layer through an adhesive, and then drilling the wave-transmitting enhancement layer by using a drill bit;
and S43, bonding the thermal control layer on the surface of the wave-transmitting enhancement layer by adopting high-temperature-resistant silica gel to achieve the final satellite surface wave-absorbing skin molding.
Compared with the prior art, the invention has the following beneficial effects:
1. the satellite surface wave-absorbing skin has larger porosity, has the characteristics of broadband wave absorption and light weight, and has small material quality loss proportion.
2. The invention can realize the characteristics of low scattering and low radiation of radar and infrared through the multilayer structure design.
Drawings
FIG. 1 is a schematic diagram of a periodic unit structure of a honeycomb wave-absorbing structure according to the present invention;
FIG. 2 is a schematic view of the shape and size of the conductive film of the present invention;
FIG. 3 is a schematic illustration of the dimensions of a honeycomb sandwich layer of the present invention;
FIG. 4 is a graph showing the reflectivity of a wave-absorbing structure according to the present invention;
fig. 5 is a flow chart of the manufacturing process of the composite material of the wave-absorbing skin of the present invention.
Detailed Description
The technical content, constructional features, achieved objects and effects of the present invention will be described in detail through preferred embodiments with reference to the accompanying drawings.
It should be noted that, the drawings are in very simplified form and all use non-precise proportions, which are only used for the purpose of conveniently and clearly assisting in describing the embodiments of the present invention, and are not intended to limit the implementation conditions of the present invention, so that the present invention has no technical significance, and any modification of structure, change of proportion or adjustment of size, without affecting the efficacy and achievement of the present invention, should still fall within the scope covered by the technical content disclosed by the present invention.
It is noted that in the present invention, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention provides a satellite surface wave-absorbing skin structure, as shown in fig. 1, wherein the wave-absorbing skin comprises four layers of structures from top to bottom: the first layer is a thermal control layer 1 and is used for preventing the surface temperature of the wave-absorbing skin from being too high due to radiation such as ultraviolet rays; the second layer is a wave-transmitting enhancement layer 2 and is mainly used as a structural enhancement layer of the wave-absorbing skin structure; the third layer is a wave-absorbing honeycomb layer 3 for realizing the characteristics of light weight and high strength for absorbing electromagnetic waves; the fourth layer, namely the bottommost layer is a reinforced shielding layer 4, and is used for isolating electromagnetic wave penetration on two sides of the wave-absorbing skin while being used as a structural reinforcing component.
Specifically, as shown in fig. 3, the wave-absorbing honeycomb layer 3 is formed by closely arranging a plurality of regular hexagonal prisms with the same shape and size, and is formed by folding and bonding paper, so as to form a honeycomb cell with a regular hexagonal cross section, wherein the side length of the inner bottom surface of each regular hexagonal prism is H, the range of H is 8 mm-12 mm, the wall thickness of each regular hexagonal prism is t, the range of t is 0.1 mm-0.3 mm, and the height of the wave-absorbing honeycomb layer 3, namely the side edge length of each regular hexagonal prism is H, the range of H is 8 mm-12 mm, and H is generally greater than or equal to H.
The wave-transmitting enhancement layer 2 is adhered to the top surface of the wave-absorbing honeycomb layer 3 through an adhesive, and a plurality of small holes are formed in the wave-transmitting enhancement layer 2, so that electromagnetic waves can enter the wave-absorbing honeycomb layer 3 through the wave-transmitting enhancement layer 2 on one hand, and on the other hand, the wave-absorbing skin is convenient to exhaust after entering vacuum; the thickness of the wave-transparent enhancement layer 2 is t 1 ，t 1 The range is 0.1 mm-0.2 mm; the reinforced shielding layer 4 is adhered to the bottom surface of the wave-absorbing honeycomb layer 3 through an adhesive, and the bottom surface of the reinforced shielding layer 4 is metallized by magnetron sputtering, so that the wave-absorbing skin has excellent shielding performance; the thickness of the reinforcing shielding layer 4 is t 2 ，t 2 The range is 0.1 mm-0.2 mm; the thermal control layer 1 is adhered to the upper surface of the wave-transparent enhancement layer 2 by an adhesive, and the thickness of the thermal control layer 1 is t 3 ，t 3 The range of (2) is 0.1mm to 0.2mm.
Further, each inner wall of the wave-absorbing honeycomb layer 3, that is, each inner wall of each regular hexagonal prism, is coated with a conductive film 5, as shown in fig. 2, the conductive film 5 is in a ring-shaped inward protruding shape (or an embedded split resonant ring), the inward protruding structures are distributed symmetrically up and down, and the center of the ring is coincident with the center of the inner wall of the wave-absorbing honeycomb layer 3. The outer diameter of the ring of the conductive film 5 is R, the range of R is 5-7 mm, the inner diameter is R, the range of R is 4-6 mm, the width of the inward protrusions is w, the range of w is 0.5-1 mm, and w=r-R (i.e. the width of the inward protrusions is equal to the ring width of the ring), the distance between two inward protrusions, i.e. the opening width is g, is 0.5-1.5 mm, the thickness of the conductive film 5 is d, the range of d is 0.02-0.04 mm, and the conductivity of the conductive film 5 is 500-1200S/m.
Further, the bottom of the inner wall of each regular hexagonal prism of the wave-absorbing honeycomb layer 3 is coated with a magnetic slurry 6, the magnetic loss of the magnetic slurry 6 is combined with the electric loss of the wave-absorbing honeycomb layer 3, so that the loss of electromagnetic waves of the wave-absorbing skin structure is improved, the wave-absorbing capacity of the wave-absorbing skin structure is further improved, and the height of the bottom of the inner wall coated with the magnetic slurry 6 is h 1 ，h 1 In the range of 1 to 2mm, the thickness t of the coated magnetic slurry 6 is 4 ，t 4 The range of (2) is 0.1-0.3 mm.
Preferably, the binder may be a phenolic resin, or a cyanate ester.
Preferably, the wave-absorbing honeycomb layer 3 can be made of aramid paper by folding and bonding.
Preferably, the material of the thermal control layer 1 has a real part of relative dielectric constant of 1.8-2.5 and an imaginary part of dielectric constant of 0.01-0.05, the thermal control layer 1 can adopt a conductive polyimide aluminized secondary surface mirror flexible thermal control film, has higher reflectivity to solar spectrum, and can reflect most of solar irradiation energy to realize the heat insulation effect of the thermal control layer 1.
Preferably, the wave-transparent reinforcing layer 2 may be glass fiber or aramid fiber.
Preferably, the reinforcing shielding layer 4 may be glass fiber, or aramid fiber, or carbon fiber.
Preferably, the magnetic slurry 6 may be a slurry formed by metal particles such as carbonyl iron, iron silicon aluminum, and the like, and epoxy resin or cyanate ester.
Preferably, the material of the conductive film 5 may be indium tin oxide, zinc aluminum oxide, or the like, or may be conductive powder such as aluminum powder, carbon powder, silver powder, copper powder, or the like, graphene particles, or a mixture of metal nanowires, phenolic resin, polyimide resin, or the like.
Preferably, the magnetron sputtered metal may be gold, silver, copper, alloys thereof, and the like.
In the preferred embodiment, in the wave-absorbing honeycomb layer 3, preferably h is 8mm, t is 0.2mm, and h is 10mm; in the wave-transparent enhancement layer 2, t is preferable 1 0.2mm; in the reinforcing shielding layer 4, t is preferable 2 0.2mm; in the thermal control layer 1, t is preferably 3 0.2mm, 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 7mm, R is 5mm, w is 1mm, g is 1mm, d is 0.04mm, and conductivity is 1200S/m; in the magnetic slurry 6, t is preferable 4 Is 0.3mm.
The designed wave-absorbing skin structure is guided into a CST software platform, reflectivity simulation is carried out on the wave-absorbing skin structure, the reflectivity of materials under vertical and horizontal polarization is analyzed, as shown in figure 4, the wave-absorbing skin structure has good wave-absorbing performance at 8-18GHz, and the reflectivity is lower than-10 dB in 8.73-18 GHz, so that the absorption of the wave-absorbing skin structure to electromagnetic waves can reach more than 90%. In addition, the wave absorbing performance curve of the wave absorbing skin structure gradually decreases with the increase of frequency, which indicates that lower reflectivity can be obtained after 18 GHz.
On the other hand, the invention also provides a preparation method of the satellite surface wave-absorbing skin structure, as shown in fig. 5, comprising the following specific steps:
s1, preparing a conductive film 5, which comprises the following steps:
s11, preparing conductive paste, which specifically comprises the following steps: firstly, mixing resin with a diluent, wherein the diluent can be acetone, absolute ethyl alcohol, nitrolacquer diluent and the like, and then mixing the diluted resin with conductive particles to obtain conductive slurry, wherein the weight ratio of the conductive particles to the resin is adjusted according to the required conductivity;
s12, screen printing, namely obtaining a conductive film by utilizing the principle that a screen plate with a pattern part penetrates through conductive paste and a screen plate without the pattern part does not penetrate through the conductive paste, wherein the method specifically comprises the following steps:
s121, cutting paper into required size;
s122, fixing and leveling a screen frame of a silk screen on a silk screen table, fixing paper on the printing table, aligning a screen plate with a ring-shaped inward protruding pattern with the paper, and adjusting the distance between the screen plate and the paper;
s123, pouring the conductive paste obtained in the step S11 on the left side of the silk screen, so that the conductive paste is extruded from the screen plate with the annular inward protruding patterns to paper;
s124, taking out the paper, standing for one minute, and leveling the conductive slurry to obtain a conductive film;
s125, heating and drying the conductive film by using an oven, wherein the drying temperature is 80-120 ℃ and the time is 5-10 minutes.
S2, printing the conductive film prepared in the step S1 on paper in a screen printing mode, and then gluing and cutting the paper.
S3, forming a wave-absorbing honeycomb layer structure, which specifically comprises the following steps:
s31, placing the paper printed with the conductive film prepared in the step S2 into a honeycomb machine for superposition, stretching and shaping to obtain a wave-absorbing honeycomb layer;
s32, soaking the magnetic slurry and curing: placing the bottom of the wave-absorbing honeycomb layer in a magnetic slurry tank with the depth of 1-2 mm, soaking for multiple times to ensure that the thickness of the soaked magnetic slurry reaches 0.1-0.3 mm, and then performing heating treatment to realize solidification of the magnetic slurry;
s33, adhesive dipping: the wave-absorbing honeycomb layer is subjected to gum dipping treatment in a gum groove of a gum dipping machine, the axial direction of a honeycomb cell is kept vertical to the horizontal plane in the gum dipping process, and thermosetting phenolic resin is generally selected as dipping liquid;
s34, heating and semi-curing: and (5) drying treatment, so that the impregnating solution reaches a semi-cured state.
S4, forming a wave-absorbing skin structure, which specifically comprises the following steps:
s41, carrying out metallization on the bottom of the enhanced shielding layer 4 by adopting magnetron sputtering, specifically, taking a corresponding metal target material as a raw material in a magnetron sputtering chamber, wherein the target material can be gold, silver, copper, alloy and the like, placing the enhanced shielding layer 4 in the sputtering chamber, arranging a magnetron cathode target support at the upper part of the sputtering chamber, arranging an observation window at the front of the sputtering chamber so as to observe the sputtering state of a sample in the sputtering process, completing the manufacture of a surface metal layer after starting up and sputtering, closing a sputtering switch, filling gas, and taking out a sample after the system is stable;
s42, bonding and curing the wave-transmitting enhancement layer 2, the wave-absorbing honeycomb layer 3 and the enhanced shielding layer 4 to realize integral molding of the wave-absorbing skin structure, and then drilling the wave-transmitting enhancement layer 2 by using a drill bit with the diameter of 1-2 mm to facilitate exhaust after the skin enters vacuum;
and S43, bonding the thermal control layer 1 on the surface of the wave-transmitting enhancement layer 2 by adopting high-temperature-resistant silica gel to achieve the final satellite wave-absorbing skin molding.
In summary, compared with the prior art, the satellite surface wave-absorbing skin structure and the preparation method thereof provided by the invention not only can realize the wave-absorbing characteristic of the broadband radar, but also have the function of resisting the vacuum environment on the basis of taking wave absorption and bearing into consideration.
While the present invention has been described in detail through the foregoing description of the preferred embodiment, it should be understood that the foregoing description is not to be considered as limiting the invention. Many modifications and substitutions of the present invention will become apparent to those of ordinary skill in the art upon reading the foregoing. Accordingly, the scope of the invention should be limited only by the attached claims.

Claims (10)

1. The satellite surface wave-absorbing skin structure is characterized by comprising four layers of structures from top to bottom:
a thermal control layer;
the surface of the wave-transmitting enhancement layer is provided with a plurality of small holes;
the wave-absorbing honeycomb layer is formed by closely arranging a plurality of regular hexagonal prisms with the same shape and size, and honeycomb cells with regular hexagons in cross section are formed;
the reinforced shielding layer is used for isolating electromagnetic wave penetration at two sides of the wave-absorbing skin;
the wave-transmitting enhancement layer is adhered to the surface of the top layer of the wave-absorbing honeycomb layer, the enhancement shielding layer is adhered to the surface of the bottom layer of the wave-absorbing honeycomb layer, and the thermal control layer is adhered to the upper surface of the wave-transmitting enhancement layer.
2. The satellite surface wave-absorbing skin structure of claim 1, wherein each inner wall of the wave-absorbing honeycomb layer is coated with a conductive film, the conductive film is in a ring inward protruding shape, the two inward protruding structures are symmetrically distributed up and down, and the center of the ring is coincident with the center of the inner wall of the wave-absorbing honeycomb layer.
3. The satellite surface wave-absorbing skin structure of claim 2, wherein the conductive film has an annular outer diameter of 5-7 mm, an inner diameter of 4-6 mm, an inward protrusion width of 0.5-1 mm, and an inward protrusion width equal to the annular width of the annular ring; the distance between two inward protrusions of the conductive film is 0.5-1.5 mm, the thickness of the conductive film is 0.02-0.04 mm, and the conductivity is 500-1200S/m.
4. The satellite surface wave-absorbing skin structure of claim 1, wherein the inner bottom side of the regular hexagonal prism is 8 mm-12 mm in length, 0.1 mm-0.3 mm in wall thickness, and 8 mm-12 mm in side edge length; the thickness of the wave-transmitting enhancement layer is 0.1 mm-0.2 mm; the thickness of the reinforced shielding layer is 0.1 mm-0.2 mm; the thickness of the thermal control layer is 0.1 mm-0.2 mm.
5. The satellite surface wave-absorbing skin structure of claim 2, wherein the magnetic paste is coated on the bottom of the inner wall of the wave-absorbing honeycomb layer, and the height of the coating is 1-2 mm, and the thickness is 0.1-0.3 mm.
6. The satellite surface wave absorbing skin structure of claim 1, wherein the bottom surface of the reinforcing shield is metallized using magnetron sputtering.
7. The satellite surface wave absorbing skin structure of claim 5,
the real part of the relative dielectric constant of the material of the thermal control layer is 1.8-2.5, and the imaginary part of the dielectric constant is 0.01-0.05;
the wave-transmitting reinforcing layer can be glass fiber and aramid fiber;
the reinforced shielding layer can be glass fiber, aramid fiber and carbon fiber;
the conductive film can be made of indium tin oxide and zinc aluminum oxide, or can be made of conductive powder such as aluminum powder, carbon powder, silver powder and copper powder, graphene particles, a mixture of metal nanowires, phenolic resin and polyimide resin;
the magnetic slurry can be slurry formed by carbonyl iron, iron silicon aluminum metal particles and epoxy resin or cyanate ester.
8. A method for preparing a satellite surface wave-absorbing skin, which is characterized by preparing the satellite surface wave-absorbing skin structure according to any one of claims 1-7, specifically comprising the following steps:
s1, preparing conductive paste, and preparing a conductive film through screen printing;
s2, printing the conductive film obtained in the step S1 on paper by screen printing to obtain paper printed with the conductive film;
s3, carrying out superposition, stretching and shaping, magnetic slurry soaking, curing, adhesive dipping and heating semi-curing treatment on the paper printed with the conductive film obtained in the step S2, so that the honeycomb structure is formed, and a wave-absorbing honeycomb layer is obtained;
and S4, sequentially bonding the thermal control layer, the wave-transmitting enhancement layer, the wave-absorbing honeycomb layer and the enhancement shielding layer from top to bottom to form a wave-absorbing skin structure.
9. The method for preparing the satellite surface wave-absorbing skin according to claim 8, wherein the preparing the conductive paste specifically comprises:
mixing resin with diluent, and mixing diluted resin with conductive particles to obtain conductive slurry, wherein the resin can be phenolic resin and polyimide resin, the diluent can be acetone, absolute ethyl alcohol and nitrolacquer diluent, and the conductive particles can be graphene particles, metal nanowires and conductive powder.
10. The method for preparing the satellite surface wave-absorbing skin according to claim 8, wherein the step S4 specifically comprises:
s41, carrying out metallization on the bottom of the enhanced shielding layer by adopting magnetron sputtering, specifically, taking a corresponding metal target material as a raw material in a magnetron sputtering chamber, placing the enhanced shielding layer in the sputtering chamber, setting a magnetron cathode target support at the upper part of the sputtering chamber, starting up to implement sputtering, completing the manufacture of the metal layer on the surface of the enhanced shielding layer, closing a sputtering switch, filling gas, and taking out the enhanced shielding layer after stabilization;
s42, sequentially laminating and curing the wave-transmitting enhancement layer, the wave-absorbing honeycomb layer and the enhanced shielding layer through an adhesive, and then drilling the wave-transmitting enhancement layer by using a drill bit;
and S43, bonding the thermal control layer on the surface of the wave-transmitting enhancement layer by adopting high-temperature-resistant silica gel to achieve the final satellite surface wave-absorbing skin molding.
CN202211430287.2A 2022-11-15 2022-11-15 Satellite surface wave-absorbing skin structure and preparation method thereof Pending CN116080218A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116916636A (en) * 2023-09-14 2023-10-20 中国空气动力研究与发展中心低速空气动力研究所 Wind tunnel balance temperature control device

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116916636A (en) * 2023-09-14 2023-10-20 中国空气动力研究与发展中心低速空气动力研究所 Wind tunnel balance temperature control device
CN116916636B (en) * 2023-09-14 2023-11-17 中国空气动力研究与发展中心低速空气动力研究所 Wind tunnel balance temperature control device

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