CN112876271B - Wave-absorbing ceramic wing rudder type component based on lossy high-temperature electromagnetic periodic structure and preparation method thereof - Google Patents
Wave-absorbing ceramic wing rudder type component based on lossy high-temperature electromagnetic periodic structure and preparation method thereof Download PDFInfo
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Abstract
The invention relates to the technical field of high-temperature resistant wave-absorbing materials, and particularly discloses a wave-absorbing ceramic wing rudder type component based on a high-temperature-consuming electromagnetic periodic structure, which sequentially comprises a bearing core layer, a continuous aluminosilicate fiber reinforced oxide ceramic matrix composite material surface layer, a high-temperature-consuming electromagnetic periodic structure wave-absorbing functional layer sintered on the surface layer, and an oxide ceramic coating outer protective layer positioned on the surface of the wave-absorbing functional layer from inside to outside; the bearing core layer is a continuous carbon fiber reinforced ceramic matrix composite or a continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite. The invention also provides a preparation method of the wave-absorbing ceramic wing rudder type component based on the lossy high-temperature electromagnetic periodic structure. The wave-absorbing ceramic wing rudder member can solve the difficult problems of the traditional technical scheme, can be applied to high-speed long-term aircrafts, has the integrated functions of high bearing, strong heat prevention, ablation resistance, low/broadband wave absorption and the like, and can obviously improve the survival and penetration capability of a new generation of aircrafts.
Description
Technical Field
The invention belongs to the technical field of high-temperature-resistant wave-absorbing materials, and particularly relates to a wave-absorbing ceramic wing rudder component based on a consumed high-temperature electromagnetic periodic structure and a preparation method thereof.
Background
The wing rudder type component is an important component of the aircraft and mainly plays key roles in controlling the stability, regulating and controlling the attitude and the like of the aircraft. Meanwhile, because the radar wave scattering property of wing rudder type components is obvious and is one of strong scattering sources on the aircraft, the aircraft is easy to detect and strike, the radar wave scattering property of the aircraft is reduced by adopting a wave-absorbing material technology, and the survival and penetration capability of the aircraft is improved. Along with the increase of the speed of the aircraft, the thermal load borne by wing rudder parts is larger and larger, and for a high-speed aircraft, wing rudder parts are required to have integrated functions of heat prevention, load bearing, ablation resistance, wave absorption and the like. The existing wing rudder type components of the high-speed aircraft mainly comprise two types: the composite material comprises a metal core layer, a resin-based composite material heat-proof outer layer and a ceramic matrix composite material member.
The wave absorbing function of the metal core layer and the resin-based composite material heat-proof outer layer is mainly realized by adding a radar absorbent into the resin-based composite material heat-proof outer layer, but the structure mainly has the following problems: 1) The uniformity of the material can be obviously influenced by the addition of the absorbent, so that the mechanical and heat-proof properties of the resin-based composite material are influenced; 2) The addition of an absorbent can add significant weight to the component; 3) The addition amount of the absorbent in the composite material is limited, and the broadband wave absorption is difficult to realize due to the electromagnetic parameter dispersion characteristic of the absorbent; 4) The applicability of the component to the high-speed long-term aircraft is poor, the wing rudder of the high-speed long-term aircraft can bear severe thermal load, and the heat-proof outer layer of the resin matrix composite material can have a serious ablation problem, so that the appearance of the wing rudder is obviously changed, and the attitude control and guidance precision of the aircraft is seriously reduced. The ceramic matrix composite component has the integrated functions of heat prevention, bearing and ablation resistance, can be applied to high-speed long-term aircrafts with severe thermal load, and at present, the component mainly adopts a continuous carbon fiber reinforced silicon carbide composite material system with high strength characteristic due to large load, but does not have stealth function due to the fact that the high conductivity characteristic of continuous carbon fiber can generate strong scattering to radar waves, and the electromagnetic scattering characteristic is similar to that of a metal component. In conclusion, the prior art schemes are difficult to realize the integrated functions of heat prevention, bearing, ablation resistance, wave absorption and the like of wing rudder members of future high-speed long-term aircrafts, and a brand new technical scheme needs to be provided.
Disclosure of Invention
The invention aims to provide a wave-absorbing ceramic wing rudder member based on a consumed high-temperature electromagnetic periodic structure and a preparation method thereof, and the wave-absorbing ceramic wing rudder member can realize the integrated functions of heat resistance, bearing, ablation resistance and wave absorption.
In order to achieve the purpose, the invention provides a wave-absorbing ceramic wing rudder type component based on a consumed high-temperature electromagnetic periodic structure, which sequentially comprises a bearing core layer, a surface layer, a consumed high-temperature electromagnetic periodic structure wave-absorbing functional layer sintered on the surface of the surface layer and an oxide ceramic coating outer protective layer positioned on the surface of the wave-absorbing functional layer from inside to outside; the bearing core layer is a continuous carbon fiber reinforced ceramic matrix composite or a continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite; the surface layer is made of a continuous aluminosilicate fiber reinforced oxide ceramic matrix composite.
Preferably, in the wave-absorbing ceramic wing rudder member, the continuous carbon fiber reinforced ceramic matrix composite reinforcement is a needle punched, sewn, 2.5D or 3D carbon fiber fabric, and the ceramic matrix is silicon carbide, silicon oxycarbide, silicon carbon nitride, silicon boron nitrogen, boron nitride or silicon boron carbon nitride; the continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite reinforcement is a needled, sewn, 2.5D or 3D silicon carbide fiber fabric, the ceramic matrix is silicon carbide, silicon-oxygen-carbon, silicon-carbon-nitrogen, silicon-boron-nitrogen, boron nitride or silicon-boron-carbon-nitrogen, and the resistivity of the silicon carbide fiber is lower than 0.1 omega-cm.
Preferably, in the wave-absorbing ceramic wing rudder type component, the continuous aluminosilicate fiber reinforced oxide composite material reinforcement is a 2.5D or 3D aluminosilicate fiber fabric with needling and sewing, the aluminosilicate fiber mainly comprises alumina, the mass content of the alumina is not less than 70%, and the oxide ceramic matrix is one or more of silica, alumina and mullite.
Preferably, in the wave-absorbing ceramic wing rudder member, the wave-absorbing functional layer with the high-temperature electromagnetic periodic structure is composed of high-temperature resistance coating patch units arranged in a periodic array, the periodic size of the patch units is 5-50mm, the thickness of the patch units is 0.01-0.05mm, and the square resistance of the patch units is 20-150 omega/\9633; the conductive phase of the high-temperature resistance coating is one or more of ruthenium dioxide, bismuth ruthenate, lead ruthenate and molybdenum disilicide, and the bonding phase is glass; the outer protective layer of the oxide ceramic coating is an alumina or mullite ceramic coating, and the thickness of the outer protective layer is 0.1 to 0.2mm.
A preparation method of the wave-absorbing ceramic wing rudder type component comprises the following steps:
(1) Preparing a fiber woven part by reserving allowance for carbon fiber or silicon carbide fiber meeting requirements according to the design size of a component, taking silicon carbide, silicon oxygen carbon, silicon carbon nitrogen, silicon boron nitrogen, boron nitride or silicon boron carbon nitrogen organic precursor solution as a dipping solution, and carrying out dipping, high-temperature cracking and repeated densification on the fiber woven part by adopting a precursor dipping cracking process to finish the preparation of a rough blank of a bearing core layer;
(2) According to the size requirement of the core layer, machining the rough blank of the bearing core layer to enable the size of the core layer to meet the requirement, and then preparing a sewing hole on the rough blank of the core layer by adopting a mechanical punching method to finish the preparation of the bearing core layer;
(3) Preparing continuous aluminosilicate fibers meeting requirements into upper and lower fiber woven pieces according to allowance reserved for component design sizes, then clamping a bearing core layer between the upper and lower fiber woven pieces, fixing the adjusting position by using a weaving tool, sewing the same continuous aluminosilicate fiber suture line on the overlapping area of the bearing core layer on the bearing core layer through a sewing hole on the bearing core layer, sewing the upper and lower fiber woven pieces in the non-overlapping area into a whole by using the continuous aluminosilicate fiber suture line, and finishing the preparation of the surface layer fiber woven piece;
(4) Repeatedly dipping, gelatinizing and thermally treating the surface layer fiber woven piece obtained in the step (3) by adopting a sol-gel method to obtain a rough blank, then machining to a designed size, and polishing the surface by adopting abrasive paper to finish the surface layer preparation;
(5) Printing high-temperature resistance coating patch units which are periodically arrayed on the surface of the surface layer obtained in the step (4) by using high-temperature resistance slurry as a raw material through a screen printing process, and preparing a high-temperature electromagnetic periodic structure wave-absorbing function layer on the surface of the surface layer through drying and sintering processes;
(6) And (3) spraying ceramic powder on the surface of the lossy high-temperature electromagnetic periodic structure by adopting a plasma spraying process to prepare an outer protective layer of an oxide ceramic coating, and then polishing to enable the thickness of the ceramic coating to meet the requirement, thereby completing the preparation of the wave-absorbing ceramic wing rudder component.
Preferably, in the above preparation method, in the step (1), the mass content of the precursor in the dipping solution is not less than 40%; the parameters of the impregnation cracking process are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800 to 1200 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5 to 1h; the densification time is not less than 10 times.
Preferably, in the preparation method, in the step (2), the aperture of the suture hole is 1.0 to 1.5mm, and the distance between the centers of the holes is 10 to 20mm.
Preferably, in the above preparation method, the stitching density of the upper and lower fiber woven fabrics in the non-overlapping region in the step (3) is 4 to 16 stitches/cm 2 。
Preferably, in the above preparation method, the specific operation of repeating the dipping, gelling, and heat treatment in the step (4) by a sol-gel method includes: clamping a surface layer fiber woven piece by using a mold, then carrying out vacuum sol impregnation, gelatinizing the surface layer fiber woven piece at the temperature of 150-200 ℃, and then carrying out heat treatment in an inert atmosphere, wherein the heat treatment process parameters are as follows: the temperature is 700-900 ℃, the processing time is 30-60min, the process is repeated for 8-12 times, the sol is one or more of silica sol, alumina sol and mullite sol, and the ceramic yield of the sol is not lower than 15wt%.
Preferably, in the above preparation method, in the step (5), the drying and sintering process parameters are: the drying temperature is 150-200 ℃, and the drying time is 0.5-1h; the sintering temperature is 500 to 850 ℃, and the sintering time is 10 to 120min;
in the step (6), the parameters of the atmospheric plasma spraying process are as follows: controlling the argon flow to be 30 to 45L/min, the hydrogen flow to be 6 to 14L/min, the current to be 500 to 600A, the power to be 32 to 42kW, the powder-conveying argon flow to be 2.0 to 5.0L/min, the powder-conveying quantity to be 20 to 40 percent and the spraying distance to be 100 to 150mm; the ceramic powder is alumina or mullite spheroidal spraying powder; the particle size of the spheroidal spray powder is 100-400 meshes, the fluidity is 40-70s, and the apparent density is 0.9-1.5g/cm 3 。
Compared with the prior art, the invention has the following beneficial effects:
1. the wave-absorbing ceramic wing rudder type component has the integrated functions of heat prevention, load bearing, ablation resistance and wave absorption, takes a continuous carbon fiber reinforced ceramic matrix composite or a continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite as a load bearing core layer, has the characteristics of high temperature resistance and high strength, and can endow the wing rudder type component with a strong load bearing function; the continuous aluminosilicate fiber reinforced oxide ceramic matrix composite material is used as a surface layer, has the characteristics of high temperature resistance, high strength, oxidation resistance and low thermal conductivity, can provide effective oxidation resistance protection for a bearing core layer, and is a dielectric material which is comprehensively designed with a consumed high-temperature electromagnetic periodic structure wave-absorbing function layer to provide excellent wave-absorbing performance for a member; in addition, the material can realize better sintering of the high-temperature-consumption electromagnetic periodic structure, so that the high-temperature-consumption electromagnetic periodic structure can be firmly attached to the surface of the layer; the wave-absorbing functional layer with the high-temperature electromagnetic periodic structure has a wider electromagnetic parameter regulation and control range by controlling the electromagnetic periodic structure parameters and the electrical performance parameters, is easy to realize broadband impedance matching, and realizes electromagnetic wave absorption by utilizing the electromagnetic loss characteristic of the high-temperature electromagnetic periodic structure, so that the limit of the traditional wave-absorbing material on the frequency dispersion characteristic of the electromagnetic parameters can be broken through, and broadband wave absorption is easier to realize; the oxide ceramic coating is an outer protective layer, has the characteristics of oxidation resistance, heat insulation and ablation resistance, and can provide effective protection for a consumed high-temperature electromagnetic periodic structure wave-absorbing functional layer.
2. The bearing core layer and the surface layer in the wave-absorbing ceramic wing rudder member realize integrated integral molding by adopting a process mode of fiber sewing and subsequent densification, and have the advantages of good integrity and high mechanical property.
3. The preparation method adopts the plasma spraying process to prepare the outer protective layer of the oxide ceramic coating, the process has the advantages of small heat damage to the base material, high deposition efficiency and the like, and the outer protective layer of the oxide ceramic coating prepared by the plasma spraying has the characteristic of porosity, so that the heat insulation performance can be improved.
4. The wave-absorbing ceramic wing rudder member can solve the problems of the traditional technical scheme, can be applied to high-speed long-term aircrafts, has the integrated functions of high bearing capacity, strong heat resistance, ablation resistance, broadband wave absorption and the like, and can remarkably improve the survival and penetration capability of a new generation of aircrafts.
Drawings
FIG. 1 is a schematic structural diagram of a wave-absorbing ceramic wing rudder type component based on a high-temperature electromagnetic periodic structure with energy consumption.
Figure 2 is a green carrier core prepared according to the present invention in example 1.
Figure 3 is a load bearing core layer prepared in example 1 of the present invention.
Fig. 4 is a face knit prepared in example 1 of the present invention.
Fig. 5 is a lossy high-temperature electromagnetic periodic structure wave-absorbing functional layer prepared in embodiment 1 of the present invention.
FIG. 6 is a photomicrograph of the alumina ceramic powder of example 1 of the present invention.
FIG. 7 shows an outer protective layer of an alumina ceramic coating prepared in example 1 of the present invention.
Description of the main reference numerals:
1-a bearing core layer, 2-a continuous aluminosilicate fiber reinforced oxide ceramic matrix composite surface layer, 3-a lossy high-temperature electromagnetic periodic structure wave-absorbing functional layer and 4-an oxide ceramic coating outer protective layer.
Detailed Description
The following detailed description of specific embodiments of the invention is provided, but it should be understood that the scope of the invention is not limited to the specific embodiments.
Example 1
A wave-absorbing ceramic wing rudder type component based on a lossy high-temperature electromagnetic periodic structure comprises a continuous carbon fiber reinforced silicon carbide ceramic matrix composite material bearing core layer 1, a continuous aluminosilicate fiber reinforced alumina composite material surface layer 2, a lossy high-temperature electromagnetic periodic structure wave-absorbing functional layer 3 sintered on the surface of the surface layer, and an alumina coating outer protective layer 4 positioned on the surface of the wave-absorbing functional layer in sequence from inside to outside as shown in figure 1. The thickness of the surface layer of the continuous aluminosilicate fiber reinforced alumina composite material in the overlapping area with the bearing core layer is 5.5mm. The continuous carbon fiber reinforced silicon carbide ceramic matrix composite reinforcement is a sewing carbon fiber woven piece, and the sewing density is 4 needles/cm 2 . The continuous aluminosilicate fiber reinforced alumina composite material reinforcement is a sewed aluminosilicate fiber fabric, and the sewing density is 4 needles/cm 2 The main component of the aluminosilicate fiber is alumina, the mass content of the alumina is 72%, and the mass content of the silica is 28%. The lossy high-temperature electromagnetic periodic structure wave-absorbing functional layer is composed of high-temperature resistance coating patch units in periodic array arrangement, the periodic size of the patch units is 20mm, the thickness of the patch units is 0.015mm, and the square resistance of the patch units is 50 omega/\9633; the conductive phase of the high-temperature resistance coating is ruthenium dioxide, and the bonding phase is glass. The thickness of the outer protective layer of the alumina coating is 0.15mm.
The embodiment also provides a preparation method of the wave-absorbing ceramic wing rudder type component based on the lossy high-temperature electromagnetic periodic structure, which comprises the following steps:
(1) The carbon fiber meeting the requirements is prepared into a fiber woven part by reserving allowance according to the design size of a component, a silicon carbide organic precursor solution is used as a dipping solution, the mass content of a polycarbosilane precursor in the dipping solution is 50%, a precursor dipping and cracking process is adopted to carry out dipping, pyrolysis and repeated densification on the fiber woven part, and the parameters of the dipping and cracking process are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 1000 ℃, the pyrolysis atmosphere is nitrogen, and the time is 1h; the densification times are 14 times, and the preparation of the rough blank of the bearing core layer is completed, as shown in figure 2;
(2) According to the size requirement of the core layer, machining the rough blank of the bearing core layer to enable the size of the core layer to meet the requirement, then preparing sewing holes on the rough blank of the core layer by adopting a mechanical punching method, wherein the aperture of each sewing hole is 1.2mm, the hole center distance is 10mm, and the preparation of the bearing core layer is finished, wherein the bearing core layer is shown in figure 3;
(3) Respectively manufacturing upper and lower fiber woven parts by reserving allowance for continuous aluminosilicate fibers meeting requirements according to the design size of a component, then clamping the bearing core layer obtained in the step (2) between the upper and lower fiber woven parts, fixing the adjusting position by adopting a weaving tool, sewing the same continuous aluminosilicate fiber suture line in the overlapped area of the bearing core layer on the bearing core layer through the sewing holes in the bearing core layer, and continuously sewing the upper and lower fiber woven parts in the non-overlapped areaThe aluminosilicate fiber suture is sewn into a whole, and the suture density is 9 needles/cm 2 Completing the preparation of the surface layer fiber woven piece, wherein the surface layer fiber woven piece is shown in figure 4;
(4) Clamping the surface layer fiber woven piece obtained in the step (3) by using a mold, then carrying out vacuum impregnation of sol, wherein the sol is alumina sol, the ceramic yield of the sol is 18wt%, gelatinizing the sol at the temperature of 200 ℃, and then carrying out heat treatment under nitrogen, and the heat treatment process parameters are as follows: the temperature is 800 ℃, the treatment time is 30min, the steps are repeated for 10 times to obtain a rough blank, then the rough blank is mechanically processed to the designed size, and the surface is polished by adopting abrasive paper to finish the preparation of the surface layer;
(5) Printing high-temperature resistance coating patch units which are periodically arrayed on the surface of the surface layer obtained in the step (4) by using high-temperature resistance paste as a raw material through a screen printing process, and then drying at 150 ℃ for 0.5h; the sintering temperature is 850 ℃, the sintering time is 10min, and a high-temperature-consuming electromagnetic periodic structure wave-absorbing functional layer is prepared on the surface of the surface layer and is shown in figure 5;
(6) Spraying alumina ceramic powder (figure 6) on the surface of the wave-absorbing functional layer with the consumed high-temperature electromagnetic periodic structure obtained in the step (5) by adopting a plasma spraying process, wherein the ceramic powder is alumina spherical spraying powder, the granularity of the spherical spraying powder is 100-400 meshes, the flowability is 58s, and the apparent density is 1.1g/cm 3 The parameters of the atmospheric plasma spraying process are as follows: controlling argon flow to be 40L/min, hydrogen flow to be 9L/min, current to be 600A, power to be 42kW, powder feeding argon flow to be 4.0L/min, powder feeding amount to be 35%, spraying distance to be 120mm, preparing an outer protective layer of the alumina ceramic coating, then polishing to enable the thickness of the ceramic coating to meet requirements, and finishing preparation of the wave-absorbing ceramic wing rudder type component.
Fig. 7 shows that the scattering characteristics (RCS) of the S and C frequency band radar of the wave-absorbing ceramic wing rudder component based on the lossy high-temperature electromagnetic periodic structure prepared in this embodiment can be reduced by more than 6dB compared with metal. The component passes the test examination and verification of 18000N and 600 ℃ thermal power combined test.
The foregoing descriptions of specific exemplary embodiments of the present invention have been presented for purposes of illustration and description. It is not intended to limit the invention to the precise form disclosed, and obviously many modifications and variations are possible in light of the above teaching. The exemplary embodiments were chosen and described in order to explain certain principles of the invention and its practical application to enable one skilled in the art to make and use various exemplary embodiments of the invention and various alternatives and modifications as are suited to the particular use contemplated. It is intended that the scope of the invention be defined by the claims and their equivalents.
Claims (6)
1. A wave-absorbing ceramic wing rudder type component based on a lossy high-temperature electromagnetic periodic structure is characterized by sequentially comprising a bearing core layer, a surface layer, a lossy high-temperature electromagnetic periodic structure wave-absorbing functional layer sintered on the surface of the surface layer and an oxide ceramic coating outer protective layer positioned on the surface of the wave-absorbing functional layer from inside to outside; the bearing core layer is a continuous carbon fiber reinforced ceramic matrix composite or a continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite, and the resistivity of the silicon carbide fiber in the continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite is lower than 0.1 omega cm; the surface layer is a continuous aluminosilicate fiber reinforced oxide ceramic matrix composite, the aluminosilicate fiber mainly contains alumina, the mass content of the alumina is not lower than 70%, and the oxide ceramic matrix is one or more of silicon oxide, alumina and mullite; the wave-absorbing functional layer with the lossy high-temperature electromagnetic periodic structure is composed of high-temperature resistance coating patch units in periodic array arrangement, the periodic size of the patch units is 5-50mm, the thickness of the patch units is 0.01-0.05mm, and the sheet resistance of the patch units is 20-150 omega/\9633; the conductive phase of the high-temperature resistance coating is one or more of ruthenium dioxide, bismuth ruthenate, lead ruthenate and molybdenum disilicide, and the binding phase is glass; the outer protective layer of the oxide ceramic coating is an alumina or mullite ceramic coating, and the thickness of the outer protective layer is 0.1 to 0.2mm;
the preparation method of the wave-absorbing ceramic wing rudder type component comprises the following steps:
(1) Preparing a fiber woven part by reserving allowance for carbon fiber or silicon carbide fiber meeting requirements according to the design size of a component, taking silicon carbide, silicon oxygen carbon, silicon carbon nitrogen, silicon boron nitrogen, boron nitride or silicon boron carbon nitrogen organic precursor solution as a dipping solution, and carrying out dipping, high-temperature cracking and repeated densification on the fiber woven part by adopting a precursor dipping cracking process to finish the preparation of a rough blank of a bearing core layer;
(2) Machining the rough blank of the bearing core layer according to the size requirement of the core layer to enable the size of the core layer to meet the requirement, then preparing a sewing hole on the rough blank of the core layer by adopting a mechanical punching method, wherein the aperture of the sewing hole is 1.0-1.5 mm, and the hole center distance is 10-20mm, and completing the preparation of the bearing core layer;
(3) Respectively manufacturing upper and lower fiber woven pieces by reserving allowance for continuous aluminosilicate fibers meeting requirements according to the design size of a component, then clamping the bearing core layer obtained in the step (2) between the upper and lower fiber woven pieces, adjusting the position by adopting a weaving tool for fixing, sewing the same continuous aluminosilicate fiber suture line as the overlapped area of the bearing core layer on the bearing core layer through a sewing hole on the bearing core layer, sewing the upper and lower fiber woven pieces in the non-overlapped area into a whole by adopting the continuous aluminosilicate fiber suture line, wherein the sewing density of the upper and lower fiber woven pieces in the non-overlapped area is 4-16 needles/cm 2 Finishing the preparation of the surface layer fiber weaving piece;
(4) Repeatedly dipping, gelatinizing and thermally treating the surface layer fiber woven piece obtained in the step (3) by adopting a sol-gel method to obtain a rough blank, wherein the specific operation steps comprise: clamping a surface layer fiber woven piece by using a mold, then carrying out vacuum sol impregnation, gelatinizing the surface layer fiber woven piece at the temperature of 150-200 ℃, and then carrying out heat treatment in an inert atmosphere, wherein the heat treatment process parameters are as follows: the temperature is 700-900 ℃, the processing time is 30-60min, the process is repeated for 8-12 times, the sol is one or more of silica sol, alumina sol and mullite sol, and the ceramic yield of the sol is not lower than 15wt%; then machining to a designed size, and polishing the surface by adopting abrasive paper to finish the preparation of a surface layer;
(5) Printing high-temperature resistance coating patch units which are periodically arrayed on the surface layer obtained in the step (4) by using high-temperature resistance slurry as a raw material through a screen printing process, and preparing a consumed high-temperature electromagnetic periodic structure wave-absorbing function layer on the surface layer through drying and sintering processes;
(6) And (3) spraying ceramic powder on the surface of the wave-absorbing functional layer with the high-temperature electromagnetic periodic structure obtained in the step (5) by adopting a plasma spraying process to prepare an outer protective layer of the oxide ceramic coating, and then polishing to enable the thickness of the ceramic coating to meet the requirement, thereby completing the preparation of the wave-absorbing ceramic wing rudder type component.
2. The wave-absorbing ceramic wing rudder member according to claim 1, wherein the continuous carbon fiber reinforced ceramic matrix composite reinforcement is a needle punched, sewn, 2.5D, 3D carbon fiber fabric, and the ceramic matrix is silicon carbide, silicon oxygen carbon, silicon carbon nitrogen, silicon boron nitrogen, boron nitride or silicon boron carbon nitrogen; the continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite reinforcement is a needled, sewn, 2.5D or 3D silicon carbide fiber fabric, and the ceramic matrix is silicon carbide, silicon-oxygen-carbon, silicon-carbon-nitrogen, silicon-boron-nitrogen, boron nitride or silicon-boron-carbon-nitrogen.
3. The wave-absorbing ceramic wing rudder type component according to claim 1, wherein the continuous aluminosilicate fiber reinforced oxide composite material reinforcement is a needled, stitched, 2.5D, 3D aluminosilicate fiber fabric.
4. The wave-absorbing ceramic wing rudder type component according to claim 1, wherein in the step (1), the mass content of a precursor in the dipping solution is not less than 40%; the parameters of the impregnation cracking process are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the high-temperature cracking temperature is 800 to 1200 ℃, the cracking atmosphere is inert atmosphere, and the time is 0.5 to 1h; the densification times are not less than 10.
5. The wave-absorbing ceramic wing rudder member according to claim 4, wherein in the step (4), the specific operation steps of repeated dipping, gelation and heat treatment by adopting a sol-gel method comprise: clamping a surface layer fiber woven piece by using a mold, then carrying out vacuum sol impregnation, gelatinizing the surface layer fiber woven piece at the temperature of 150-200 ℃, and then carrying out heat treatment in an inert atmosphere, wherein the heat treatment process parameters are as follows: the temperature is 700-900 ℃, the processing time is 30-60min, the process is repeated for 8-12 times, the sol is one or more of silica sol, alumina sol and mullite sol, and the ceramic yield of the sol is not lower than 15wt%.
6. The wave-absorbing ceramic wing rudder type component according to claim 1, wherein in the step (5), the drying and sintering process parameters are as follows: the drying temperature is 150-200 ℃, and the drying time is 0.5-1h; the sintering temperature is 500 to 850 ℃, and the sintering time is 10 to 120min;
in the step (6), the parameters of the atmospheric plasma spraying process are as follows: controlling the argon flow to be 30 to 45L/min, the hydrogen flow to be 6 to 14L/min, the current to be 500 to 600A, the power to be 32 to 42kW, the powder-feeding argon flow to be 2.0 to 5.0L/min, the powder-feeding quantity to be 20 to 40 percent and the spraying distance to be 100 to 150mm; the ceramic powder is alumina or mullite spheroidal spraying powder; the particle size of the spheroidal spray coating powder is 100 to 400 meshes, the fluidity is 40 to 70s, and the apparent density is 0.9 to 1.5g/cm 3 。
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