CN113911401A - Light/high-temperature-resistant integrated composite material satellite lens hood and preparation method thereof - Google Patents
Light/high-temperature-resistant integrated composite material satellite lens hood and preparation method thereof Download PDFInfo
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- CN113911401A CN113911401A CN202111164701.5A CN202111164701A CN113911401A CN 113911401 A CN113911401 A CN 113911401A CN 202111164701 A CN202111164701 A CN 202111164701A CN 113911401 A CN113911401 A CN 113911401A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/54—Protection against radiation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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Abstract
The invention discloses a light/high-temperature-resistant integrated composite material satellite lens hood and a preparation method thereof. The traditional satellite lens hood is made of metal materials, and cannot meet the harsh requirements of a novel satellite on low density, high temperature resistance, low linear expansion coefficient and the like. The invention relates to a composite material satellite shade which is formed by respectively dividing a product into a base and a strap, and then combining the base and the strap into a whole through a sleeving and bonding process. The base is prepared by the working procedures of preparing medium/low density prepreg, cutting the prepreg, laying the prepreg at 0 degree/90 degree, curing the autoclave and the like. The strap is prepared by the working procedures of prepreg slitting, prepreg cloth tape winding, core mold preparation, cloth tape parallel winding, autoclave curing and the like. And combining the base and the strap by adopting a high-temperature-resistant adhesive to obtain the light shield. The composite material satellite shade has the advantages of light weight, high temperature resistance, small linear expansion coefficient, high specific strength, large specific modulus, long service life and the like, and is verified by ground experiments such as vibration, impact and the like.
Description
Technical Field
The invention belongs to the technical field of satellite composite materials and processes, and particularly relates to a light/high-temperature-resistant integrated composite material satellite hood and a preparation method thereof.
Background
The satellite light shield is used for reducing the irradiation energy of non-target rays such as solar stray light, earth gas stray light or internal stray light and the like, thereby reducing the interference on the star sensor. The traditional satellite lens hood is an integral structure product made of metal, and can not meet the rigorous requirements of new types of satellites on low density, high temperature resistance, high strength, high modulus, low expansion coefficient and other performances. The advanced composite material has the characteristics of strong designability and the like, and can be used for developing a composite material with low density, high temperature resistance and high dimensional stability as a substitute. Meanwhile, the working condition of the satellite also requires that the composite material satellite lens hood has the excellent characteristics of ablation resistance, low thermal conductivity, small linear expansion coefficient, high specific strength, large specific modulus, long service life, no volatile micromolecule overflow under vacuum, three prevention, vibration resistance, impact resistance and the like.
Disclosure of Invention
In order to overcome the defects of the existing metal satellite light shield, the invention provides a light/high temperature resistant integrated composite material satellite light shield and a preparation method thereof.
The technical scheme adopted by the invention is that a light high-strength high-temperature-resistant low-heat-conduction composite material is used as a substitute material, and the thin-wall round shell characteristic of the product structure of the satellite sunshade is combined, so that a forming scheme is designed, wherein the product is split into a composite material base with a laminated plate structure and a composite material strap with a cloth belt winding round ring structure, and then the two components are sleeved and bonded into a whole through a high-temperature-resistant adhesive. The high-temperature-resistant laminated composite material base is prepared by the procedures of glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg laying, autoclave curing and machining; the high-temperature-resistant strap wound composite material strap is prepared by the procedures of glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg tape winding, core mold preparation, tape parallel winding, autoclave curing and machining. And combining the high-temperature-resistant laminated composite material base and the high-temperature-resistant cloth belt wound composite material strap into a whole by adopting a high-temperature-resistant adhesive through a sleeving and bonding process to obtain the sunshade.
Preferably, the product structure of the composite material base is 0°/90°Laminate structure of the ply. The fiber type of the reinforcement in the composite material system is one or more combinations of alkali-free glass fiber cloth, Wlan cloth, high silica fiber cloth, quartz fiber cloth, carbon fiber cloth and inorganic-organic mixed woven fiber cloth, and the weave form is one or more combinations of plain weave, twill weave and satin weave fiber cloth. The substrate is hot meltThe resin includes one or more of phenolic resin, benzoxazine resin, phenolic-epoxy resin, ceramifiable phenolic resin, bismaleimide resin, cyanate resin, polyimide resin, phthalonitrile resin, polysilazane resin, polycarbosilane resin and silicon-containing aryne resin. The filler is one or a combination of phenolic beads, glass beads, ceramic beads, metal oxide, silicate, ceramic filler and low-melting-point glass powder.
Preferably, the product structure of the composite material belt is a cloth tape winding circular ring structure. The fiber type of the reinforcement in the composite material system is one or more combinations of alkali-free glass fiber cloth, Wlan cloth, high silica fiber cloth, quartz fiber cloth, carbon fiber cloth and inorganic-organic mixed woven fiber cloth, and the weave form is one or more combinations of plain weave, twill weave and satin weave fiber cloth. The matrix is hot melt resin, and comprises one or more of phenolic resin, benzoxazine resin, phenolic-epoxy resin, porcelainized phenolic resin, bismaleimide resin, cyanate resin, polyimide resin, phthalonitrile resin, polysilazane resin, polycarbosilane resin and silicon-containing aryne resin. The filler is one or a combination of phenolic beads, glass beads, ceramic beads, metal oxide, silicate, ceramic filler and low-melting-point glass powder.
Another aspect of the present invention provides a method for preparing the above composite material satellite shade, comprising the steps of:
s1, preparing a high-temperature-resistant laminated composite material base by glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg laying, autoclave curing and machining;
s2, preparing a high-temperature-resistant cloth belt wound composite material strap by using glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg cloth belt winding, core mold preparation, cloth belt parallel winding, autoclave curing and machining procedures;
and S3, combining the high-temperature-resistant laminated composite material base and the high-temperature-resistant cloth belt wound composite material strap into a whole by adopting a high-temperature-resistant adhesive through a sleeving and bonding process.
Preferably, the prepreg in the step S1 is prepared by a two-step method and a two-film method in a hot-melt method prepreg process, the resin is heated to melt and mixed with the filler, then the adhesive film is prepared by an adhesive film machine, and finally the prepreg is prepared by a compound machine according to the laminating sequence of the adhesive film, the fiber fabric and the adhesive film, wherein the resin content of the prepared prepreg is (33 ± 3)%, and the volatile content is less than or equal to 1.2%; cutting the prepreg into cloth blocks; the prepreg ply angle is 0 degree/90 degrees; the autoclave process curing system is as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature (170-200) DEG C, and curing time is calculated as follows: t is the heat preservation time in the unit of min, a is the value range of 4-6 in the unit of min/mm, and d is the thickness of the blank laminated board in the unit of mm; the mechanical processing is to process the composite material laminating blank to a required size, and the cloth layer direction is vertical to the height direction of the base.
Preferably, the prepreg in the step S2 is prepared by a two-step method and a two-film method in a hot-melt method prepreg process, the resin is heated to melt and mixed with the filler, then the adhesive film is prepared by an adhesive film machine, and finally the prepreg is prepared by a compound machine according to the laminating sequence of the adhesive film, the fiber fabric and the adhesive film, wherein the resin content of the prepared prepreg is (40 ± 3)%, and the volatile content is less than or equal to 1.2%; cutting a cloth belt with the shape of 30mm or 40mm width from the prepreg; the prepreg winding method comprises the steps of firstly binding long cloth belts together through nylon fibers, and then winding the long cloth belts on a paper tube; the winding is to wind the cloth belt on the metal core mould by adopting a parallel cloth belt winding process, and the process parameters are as follows: 30mm (90-150) N of cloth belt tension, 40mm (120-200) N of cloth belt tension, 9-11 mm/rotation of overlapping allowance and 70-110 ℃ of preheating temperature; the autoclave process curing system is as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature (170-200) DEG C, and curing time is calculated as follows: t is the heat preservation time in the unit of min, a is the value range of 4-6 in the unit of min/mm, and d is the thickness of the blank cylinder in the unit of mm; and the mechanical processing is to process the composite material tape winding blank to a required size.
Preferably, the prepreg in steps S1 and S2 needs to be compounded before the adhesive film is prepared, that is, the resin after being heated and melted is blended with the low-density filler and the porcelain-forming filler and stirred uniformly, and low-density modification, modification for improving heat insulation performance and porcelainizing heat-proof modification are performed.
Preferably, the high temperature resistant adhesive in step S3 is one or more of an epoxy system adhesive, a phenolic-epoxy system adhesive, an organosilicon system adhesive, a polyimide system adhesive, and a ceramifiable phenolic adhesive.
Preferably, the curing system of the package bonding in step S3 is: curing at room temperature for 12h or (70 +/-10) DEG C for (1-5) h.
Compared with the prior art, the invention has the following beneficial effects:
1. the composite material satellite shade is formed by dividing a product into a base and a strap, and then combining the base and the strap into a whole through a sleeving and bonding process. The high-temperature-resistant laminated composite material base is prepared by the procedures of glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg laying, autoclave curing, machining and the like. The high-temperature-resistant strap wound composite material strap is prepared by the procedures of glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg strap winding, core mold preparation, strap parallel winding, autoclave curing, machining and the like. Combining a high-temperature-resistant laminated composite material base and a high-temperature-resistant cloth belt wound composite material strap into a whole by adopting a high-temperature-resistant adhesive through a sleeving and bonding process to obtain a light shield;
2. the composite material satellite lens hood has the characteristics of light weight and high temperature resistance, overcomes the defects of the traditional metal satellite lens hood, has the advantages of ablation resistance, low thermal conductivity, small linear expansion coefficient, high specific strength, large specific modulus, long service life, no volatile micromolecules overflow under vacuum and the like, and is verified and successfully carried out through ground experiments of three prevention, vibration, impact and the like;
3. the composite material satellite shade uses a light high-strength high-temperature-resistant low-heat-conductivity composite material as a substitute material, develops the medium-density high-temperature-resistant hot-melt prepreg according to the model requirement, and develops the low-density high-temperature-resistant prepreg through low-density modification innovativeness;
4. the invention designs an innovative forming scheme that the product is split into a composite material base with a laminated plate structure and a composite material strap with a strap winding circular ring structure by combining the characteristics of a thin-wall circular shell of a satellite lens hood product structure, and then the two components are sleeved and bonded into a whole through a high-temperature-resistant adhesive.
Drawings
FIG. 1 is a schematic structural diagram of a composite satellite light shield in accordance with an embodiment of the present invention;
FIG. 2 is a flow chart of the preparation of the composite material satellite shade of example 1 of the present invention;
FIG. 3 is a film of the composite material of the satellite shade of example 1 of the present invention;
FIG. 4 is a prepreg of a composite satellite shade of example 1 of the present invention;
FIG. 5 is a density measurement report of a composite satellite shade obtained in example 1 of the present invention;
FIG. 6 is a glass transition temperature test curve of the composite satellite shade obtained in example 1 of the present invention;
FIG. 7 is a thermal conductivity measurement report of a composite satellite shade obtained in example 1 of the present invention;
fig. 8 is a report of the average linear expansion coefficient of the composite satellite shade obtained in example 1 of the present invention.
Fig. 9 is a report of the tensile properties of the composite satellite shade obtained in example 1 of the present invention.
Fig. 10 is a report of the compression performance test of the composite satellite shades obtained in example 1 of the present invention.
Fig. 11 is a bending performance test report of the composite satellite shade obtained in example 1 of the present invention.
Wherein: 1-a composite laminate base; 2-winding the belt with the composite material belt.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
The composite material satellite shade provided by the embodiment is prepared from quartz cloth, cyanate ester and glass beads.
The preparation method specifically comprises the following steps:
1. putting the hot-melt cyanate ester resin into an oven at 70 +/-5 ℃ for heating for 30-40 min to be completely melted;
2. uniformly stirring the molten cyanate and S38 glass hollow microspheres in a ratio of 3:1 by using a vertical dispersion machine to prepare a glue solution;
3. preparing the glue solution with the breadth of 1m and the surface density of (140 +/-5) g/m by a glue film machine2The glue film comprises the following gluing technological parameters: the gluing temperature is 70 +/-2 ℃, and the production speed is 3-5 m/min;
4. the surface density of the upper and lower layers of glue films and the fiber is (70 +/-5) g/m2The twill quartz cloth is prepared by a compound machine, and has the width of 1m and the surface density of (350 +/-10) g/m2The low-density quartz cloth/cyanate ester hot-melt prepreg has the following composite technological parameters: the temperature of the composite roller is 95, 90 and 85 ℃, the gap between the composite rollers is 480, 430 and 380 mu m, and the production speed is 3-6 m/min;
5. will be 4m2Cutting the prepreg into 90 pieces of cloth with the size of 200mm multiplied by 200mm by a cloth cutting machine, and stacking the cloth pieces according to the angle of 0 degree/90 degrees;
6. vacuum-coating the laminated body, namely sequentially covering 1 layer of porous membrane and 4 layers of adhesive absorption felts on the surface of a sample plate, then coating the bottom surface of a steel plate with 1 layer of adhesive absorption felts, and fixing with an adhesive tape; secondly, sealing the sample by using a vacuum bag, and reserving an outlet before sealing so as to be convenient for installing a vacuum nozzle; cutting 1 piece of 20cm × 20cm air-permeable felt, folding the air-permeable felt in half, then leading out the air-permeable felt from a non-sample area to be vertical to a sample plate, and then installing a vacuum nozzle on the air-permeable felt to prevent the vacuum nozzle from being blocked during curing; fourthly, sealing the vacuum bag;
7. and (3) curing the superposed body by adopting an autoclave process, wherein the process parameters are as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature (170-200) DEG C, and curing time 75 min;
8. machining the composite material laminated blank to a required size to obtain a base, wherein the direction of a laminated board cloth layer is vertical to the height direction of the base;
9. will be 5m2Cutting the prepreg into cloth belts with the width of 30mm, binding the cloth belts together by using a nylon thread through a sewing machine, and pouring the cloth belts into a disc by using a winding machine;
10. and winding a 30mm cloth tape on a phi 110mm core die by a cloth tape winding machine according to a parallel winding process, wherein the winding outer diameter is larger than 135 mm. The cloth tape winding process parameters are as follows: the tension of a 30mm cloth belt is (90-150) N, the overlapping allowance is (9-11) mm/rotation, and the preheating temperature is (70-110) DEG C;
11. the winding body is coated with vacuum firstly, 1 layer of porous membrane and 4 layers of adhesive absorption felts are sequentially covered on the surface of a sample plate, then the bottom surface of the steel plate is coated with 1 layer of adhesive absorption felts and is fixed by an adhesive tape; secondly, sealing the sample by using a vacuum bag, and reserving an outlet before sealing so as to be convenient for installing a vacuum nozzle; cutting 1 piece of 20cm × 20cm air-permeable felt, folding the air-permeable felt in half, then leading out the air-permeable felt from a non-sample area to be vertical to a sample plate, and then installing a vacuum nozzle on the air-permeable felt to prevent the vacuum nozzle from being blocked during curing; fourthly, sealing the vacuum bag;
12. and (3) curing the superposed body by adopting an autoclave process, wherein the process parameters are as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature (170-200) DEG C, and curing time 60 min;
13. processing the composite material cloth tape winding blank to a required size by machining to obtain a strap;
14. polishing the bonding surface of the base and the strap roughly by using (36-60) mesh abrasive paper, cleaning by using alcohol, and airing at room temperature for 1 h;
15. and (5) adhesive allocation.
TABLE 1
| Material | Mass ratio of |
| E51 epoxy | 100 portions of |
| |
10 to 30 portions of |
| |
5 to 15 parts of |
| Tetraethylenepentamine | 22 to 25 portions of |
| White carbon black | 40 to 50 portions of |
| |
10 to 15 portions of |
16. Protecting the non-bonding surface of the base and the strap by using tetrafluoro release cloth;
17. and coating an adhesive on the bonding surface of the base and the strap, sleeving by adopting an auxiliary tool, and curing for 12 hours at room temperature.
The composite material satellite shade obtained in the embodiment is detected to have the density of 0.96g/cm3A glass transition temperature of 360 ℃, a thermal conductivity of 0.201W/(m.K), and an average linear expansion coefficient of 7.2X 10-6/° C, tensile strength 39.2MPa, compressive strength 142MPa, and flexural strength 93.5 MPa.
Example 2
The composite material satellite shade described in this embodiment is prepared from high silica cloth and phenolic resin.
The preparation method specifically comprises the following steps:
1. putting the hot-melt phenolic aldehyde into an oven at the temperature of (65 +/-5) DEG C, and heating for 30-40 min to completely melt the phenolic aldehyde;
2. preparing the glue solution with the breadth of 1m and the surface density of (85 +/-5) g/m by a glue film machine2The glue film comprises the following gluing technological parameters: the gluing temperature is 65 +/-2 ℃, and the production speed is 3-5 m/min;
3. the surface density of the upper and lower layers of glue films and the fiber is (260 +/-5) g/m2The plain high silica cloth is prepared by a compounding machine, and has the width of 1m and the surface density of (530 +/-10) g/m2The low-density quartz cloth/cyanate ester hot-melt prepreg has the following composite technological parameters: the temperature of the composite roller is 85, 80 and 75 ℃ in sequence, the clearance of the composite roller is 520, 470 and 420 mu m in sequence, and the production speed is 3-6 m/min;
4. will be 4m2Cutting the prepreg into 90 pieces of cloth with the size of 200mm multiplied by 200mm by a cloth cutting machine, and stacking the cloth pieces according to the angle of 0 degree/90 degrees;
5. vacuum-coating the laminated body, namely sequentially covering 1 layer of porous membrane and 4 layers of adhesive absorption felts on the surface of a sample plate, then coating the bottom surface of a steel plate with 1 layer of adhesive absorption felts, and fixing with an adhesive tape; secondly, sealing the sample by using a vacuum bag, and reserving an outlet before sealing so as to be convenient for installing a vacuum nozzle; cutting 1 piece of 20cm × 20cm air-permeable felt, folding the air-permeable felt in half, then leading out the air-permeable felt from a non-sample area to be vertical to a sample plate, and then installing a vacuum nozzle on the air-permeable felt to prevent the vacuum nozzle from being blocked during curing; fourthly, sealing the vacuum bag;
6. and (3) curing the superposed body by adopting an autoclave process, wherein the process parameters are as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature 175 ℃, and curing time 75 min;
7. machining the composite material laminated blank to a required size to obtain a base, wherein the direction of a laminated board cloth layer is vertical to the height direction of the base;
8. will be 5m2Cutting the prepreg into cloth belts of 30mm, binding the cloth belts together by a sewing machine through nylon threads, and turning the cloth belts into discs by a winding machine;
9. and winding a 30mm cloth tape on a phi 110mm core die by a cloth tape winding machine according to a parallel winding process, wherein the winding outer diameter is larger than 135 mm. The cloth tape winding process parameters are as follows: the tension of a 30mm cloth belt is (90-150) N, the overlapping allowance is (9-11) mm/rotation, and the preheating temperature is (70-110) DEG C;
10. the winding body is coated with vacuum firstly, 1 layer of porous membrane and 4 layers of adhesive absorption felts are sequentially covered on the surface of a sample plate, then the bottom surface of the steel plate is coated with 1 layer of adhesive absorption felts and is fixed by an adhesive tape; secondly, sealing the sample by using a vacuum bag, and reserving an outlet before sealing so as to be convenient for installing a vacuum nozzle; cutting 1 piece of 20cm × 20cm air-permeable felt, folding the air-permeable felt in half, then leading out the air-permeable felt from a non-sample area to be vertical to a sample plate, and then installing a vacuum nozzle on the air-permeable felt to prevent the vacuum nozzle from being blocked during curing; fourthly, sealing the vacuum bag;
11. and (3) curing the superposed body by adopting an autoclave process, wherein the process parameters are as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature 175 ℃ and curing time 60 min;
12. processing the composite material cloth tape winding blank to a required size by machining to obtain a strap;
13. polishing the bonding surface of the base and the strap roughly by using (36-60) mesh abrasive paper, cleaning by using alcohol, and airing at room temperature for 1 h;
14. and (5) adhesive allocation.
TABLE 2
| Material | Mass ratio of |
| E51 epoxy | 100 portions of |
| |
10 to 30 portions of |
| |
5 to 15 parts of |
| Tetraethylenepentamine | 22 to 25 portions of |
| White carbon black | 40 to 50 portions of |
| |
10 to 15 portions of |
15. Protecting the non-bonding surface of the base and the strap by using tetrafluoro release cloth;
16. and coating an adhesive on the bonding surface of the base and the strap, sleeving by adopting an auxiliary tool, and curing for 12 hours at room temperature.
Performance test of composite material satellite lens hood
The composite satellite shade obtained in each of the above examples was tested for density, glass transition temperature, thermal conductivity, average linear expansion coefficient, tensile strength, compressive strength, and flexural strength, and the test results are shown in table 3.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
TABLE 3 composite material satellite lens hood Performance test
Claims (9)
1. A composite material satellite lens hood and a preparation method thereof are characterized in that:
the composite material satellite shade is formed by dividing a product into a base and a strap which are respectively formed and then combined into a whole through a sleeving and bonding process. The high-temperature-resistant laminated composite material base is prepared by the procedures of glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg laying, autoclave curing, machining and the like. The high-temperature-resistant strap wound composite material strap is prepared by the procedures of glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg strap winding, core mold preparation, strap parallel winding, autoclave curing, machining and the like. And combining the high-temperature-resistant laminated composite material base and the high-temperature-resistant cloth belt wound composite material strap into a whole by adopting a high-temperature-resistant adhesive through a sleeving and bonding process to obtain the sunshade.
2. The composite satellite shade of claim 1, wherein:
the product structure of the composite material base is 0°Laminated board structure of/90 degree ply. The fiber type of the reinforcement in the composite material system is one or more combinations of alkali-free glass fiber cloth, Wlan cloth, high silica fiber cloth, quartz fiber cloth, carbon fiber cloth and inorganic-organic mixed woven fiber cloth, and the weave form is one or more combinations of plain weave, twill weave and satin weave fiber cloth. The matrix is hot melt resin, and the types of the hot melt resin comprise one or more of phenolic resin, benzoxazine resin, phenolic-epoxy resin, porcelainized phenolic resin, bismaleimide resin, cyanate resin, polyimide resin, phthalonitrile resin, polysilazane resin, polycarbosilane resin and silicon-containing aryne resin. The filler is one or a combination of phenolic beads, glass beads, ceramic beads, metal oxide, silicate, ceramic filler and low-melting-point glass powder.
3. The composite satellite shade of claim 1, wherein:
the product structure of the composite material strap is a cloth belt winding circular ring structure. The fiber type of the reinforcement in the composite material system is one or more combinations of alkali-free glass fiber cloth, Wlan cloth, high silica fiber cloth, quartz fiber cloth, carbon fiber cloth and inorganic-organic mixed woven fiber cloth, and the weave form is one or more combinations of plain weave, twill weave and satin weave fiber cloth. The matrix is hot melt resin, and comprises one or more of phenolic resin, benzoxazine resin, phenolic-epoxy resin, porcelainized phenolic resin, bismaleimide resin, cyanate resin, polyimide resin, phthalonitrile resin, polysilazane resin, polycarbosilane resin and silicon-containing aryne resin. The filler is one or a combination of phenolic beads, glass beads, ceramic beads, metal oxide, silicate, ceramic filler and low-melting-point glass powder.
4. A method of making a composite satellite shade according to any of claims 1-3, comprising the steps of:
s1, preparing a high-temperature-resistant laminated composite material base by glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg laying, autoclave curing and machining;
s2, preparing a high-temperature-resistant cloth belt wound composite material strap by using glue preparation, glue film preparation, medium/low-density prepreg preparation, prepreg cutting, prepreg cloth belt winding, core mold preparation, cloth belt parallel winding, autoclave curing and machining procedures;
and S3, combining the high-temperature-resistant laminated composite material base and the high-temperature-resistant cloth belt wound composite material strap into a whole by adopting a high-temperature-resistant adhesive through a sleeving and bonding process.
5. The method of making a composite satellite shade according to claim 4, wherein:
pre-impregnation in step S1The material is prepared by adopting a two-step method and a two-film method in a hot-melt method pre-dipping process, firstly, resin is heated and melted and is mixed with filler, then an adhesive film is prepared by adopting an adhesive film machine, finally, a compound machine is adopted to carry out pre-dipping according to the laminating sequence of the adhesive film, the fiber fabric and the adhesive film, and the resin content of the prepared pre-dipping material is (33 +/-3)%, and the volatile matter content is less than or equal to 1.2%; cutting the prepreg into cloth blocks; the prepreg lay-up angle is 0°/90°(ii) a The autoclave process curing system is as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature (170-200) DEG C, and curing time is calculated as follows: t is the heat preservation time in the unit of min, a is the value range of 4-6 in the unit of min/mm, and d is the thickness of the blank laminated board in the unit of mm; the mechanical processing is to process the composite material laminating blank to a required size, and the cloth layer direction is vertical to the height direction of the base.
6. The method of making a composite satellite shade according to claim 4, wherein:
the prepreg in the step S2 is prepared by adopting a two-step method and a two-film method in a hot-melt method prepreg process, firstly, resin is heated to melt and mixed with filler, then an adhesive film is prepared by adopting an adhesive film machine, and finally, a compound machine is adopted to carry out prepreg according to the laminating sequence of the adhesive film, the fiber fabric and the adhesive film, wherein the resin content of the prepared prepreg is (40 +/-3)%, and the volatile matter content is less than or equal to 1.2%; cutting a cloth belt with the shape of 30mm or 40mm width from the prepreg; the prepreg winding method comprises the steps of firstly binding long cloth belts together through nylon fibers, and then winding the long cloth belts on a paper tube; the winding is to wind the cloth belt on the metal core mould by adopting a parallel cloth belt winding process, and the process parameters are as follows: 30mm (90-150) N of cloth belt tension, 40mm (120-200) N of cloth belt tension, 9-11 mm/rotation of overlapping allowance and 70-110 ℃ of preheating temperature; the autoclave process curing system is as follows: molding pressure (1-3) MPa, heating rate (0.3-0.5) DEG C/min, molding temperature (170-200) DEG C, and curing time is calculated as follows: t is the heat preservation time in the unit of min, a is the value range of 4-6 in the unit of min/mm, and d is the thickness of the blank cylinder in the unit of mm; and the mechanical processing is to process the composite material tape winding blank to a required size.
7. The method of making a composite satellite shade according to claim 4, wherein:
in the steps S1 and S2, the prepreg needs to be matched with glue before the glue film is prepared, namely, the resin after being heated and melted is mixed with the low-density filler and the porcelain forming filler and is stirred uniformly, and low-density modification, modification for improving heat insulation performance and porcelainizing heat-proof modification are carried out.
8. The method of making a composite satellite shade according to claim 4, wherein:
in the step S3, the high temperature resistant adhesive is one or a combination of epoxy system adhesive, phenolic aldehyde-epoxy system adhesive, organic silicon system adhesive, polyimide system adhesive and porcelainable phenolic adhesive.
9. The method of making a composite satellite shade according to claim 4, wherein:
the curing system of the set bonding in the step S3 is as follows: curing at room temperature for 12h or (70 +/-10) DEG C for (1-5) h.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115678275A (en) * | 2022-11-09 | 2023-02-03 | 航天特种材料及工艺技术研究所 | Bismaleimide resin for autoclave zero-suction-rubber molding prepreg and preparation method thereof |
| CN118006124A (en) * | 2024-04-09 | 2024-05-10 | 北京玻钢院复合材料有限公司 | Prepreg for preparing composite antenna housing, composite antenna housing and preparation method thereof |
-
2021
- 2021-09-30 CN CN202111164701.5A patent/CN113911401A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115678275A (en) * | 2022-11-09 | 2023-02-03 | 航天特种材料及工艺技术研究所 | Bismaleimide resin for autoclave zero-suction-rubber molding prepreg and preparation method thereof |
| CN118006124A (en) * | 2024-04-09 | 2024-05-10 | 北京玻钢院复合材料有限公司 | Prepreg for preparing composite antenna housing, composite antenna housing and preparation method thereof |
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