CN114523688A - Long-time heat-proof composite material, preparation method and application - Google Patents
Long-time heat-proof composite material, preparation method and application Download PDFInfo
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- CN114523688A CN114523688A CN202011323534.XA CN202011323534A CN114523688A CN 114523688 A CN114523688 A CN 114523688A CN 202011323534 A CN202011323534 A CN 202011323534A CN 114523688 A CN114523688 A CN 114523688A
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- 239000002131 composite material Substances 0.000 title claims abstract description 35
- 238000002360 preparation method Methods 0.000 title claims abstract description 12
- 230000007774 longterm Effects 0.000 claims abstract description 28
- 238000009413 insulation Methods 0.000 claims abstract description 17
- 238000002679 ablation Methods 0.000 claims abstract description 15
- 238000000034 method Methods 0.000 claims abstract description 9
- 238000009461 vacuum packaging Methods 0.000 claims abstract description 4
- 239000010410 layer Substances 0.000 claims description 38
- 239000004744 fabric Substances 0.000 claims description 30
- 239000000835 fiber Substances 0.000 claims description 23
- 229920005989 resin Polymers 0.000 claims description 18
- 239000011347 resin Substances 0.000 claims description 18
- 239000002344 surface layer Substances 0.000 claims description 15
- 239000010453 quartz Substances 0.000 claims description 13
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 13
- 239000005011 phenolic resin Substances 0.000 claims description 11
- 229920001568 phenolic resin Polymers 0.000 claims description 11
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 7
- CMLFRMDBDNHMRA-UHFFFAOYSA-N 2h-1,2-benzoxazine Chemical compound C1=CC=C2C=CNOC2=C1 CMLFRMDBDNHMRA-UHFFFAOYSA-N 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- 239000003365 glass fiber Substances 0.000 claims description 6
- 239000012792 core layer Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 229920001721 polyimide Polymers 0.000 claims description 5
- 239000009719 polyimide resin Substances 0.000 claims description 5
- 238000009941 weaving Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 abstract description 17
- 238000004806 packaging method and process Methods 0.000 description 4
- 238000005498 polishing Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000004753 textile Substances 0.000 description 2
- 239000004964 aerogel Substances 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
- B64G1/58—Thermal protection, e.g. heat shields
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- General Health & Medical Sciences (AREA)
- Health & Medical Sciences (AREA)
- Thermal Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Emergency Medicine (AREA)
- Critical Care (AREA)
- Moulding By Coating Moulds (AREA)
- Reinforced Plastic Materials (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to the technical field of composite materials, and discloses a long-term heat-proof composite material, and a preparation method and application thereof. The preparation method comprises the following steps: preparing a hollow heat insulation layer, laying ablation-resistant prepreg on the surface of the hollow heat insulation layer, and carrying out vacuum packaging and curing to obtain the long-term heat-proof composite material. The long-term heat-proof material prepared by the method has a controllable structure, and can be used for designing heat-insulating layers with different thicknesses and different types of ablation-resistant composite material heat-proof layers according to different use environments.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to a long-term heat-proof composite material, and a preparation method and application thereof.
Background
The description of the background of the invention pertaining to the related art to which this invention pertains is given for the purpose of illustration and understanding only of the summary of the invention and is not to be construed as an admission that the applicant is explicitly or implicitly admitted to be prior art to the date of filing this application as first filed with this invention.
The heat protection material on the surface of the aircraft has the function of reducing the heat energy entering the aircraft as much as possible, so that the internal components of the aircraft can normally work within a reasonable temperature range. Another requirement as a good insulating material is that there should be no air flow in the material, as air flow will cause heat to be dissipated in the form of convection. The fibers have a large specific surface area and the surface friction can considerably impede the air flow. The factor influencing the heat-insulating property of the material is the internal structure of the textile, and the factor influencing the heat-insulating property of the material is the internal structure of the textile.
The three-dimensional hollow fabric can be woven by adopting various high-performance continuous fibers such as glass fibers, carbon fibers, aramid fibers and the like, the sandwich structure is based on warp and weft yarns forming surface layers and Z-direction fibers connecting the two surface layers and forming a core part, the weaving height range of the hollow fabric is 2-50mm, and the spatial form can be arbitrarily designed into a shape like a Chinese character '8', 'mouth', 'V', and the like according to the use requirement of the composite material. It has good impact resistance, and can be widely applied to rail transit, ships and boats, aviation, aerospace, wind energy, buildings, double-layer storage tanks and the like.
Disclosure of Invention
The embodiment of the invention aims to provide a long-time heat-proof composite material, and a preparation method and application thereof. The long-term heat-proof material prepared by the method has a controllable structure, and can be used for designing heat-insulating layers with different thicknesses and different types of ablation-resistant composite material heat-proof layers according to different use environments.
The purpose of the embodiment of the invention is realized by the following technical scheme:
a preparation method of a long-time heat-proof composite material comprises the following steps:
preparing a hollow heat insulation layer, laying ablation-resistant prepreg on the surface of the hollow heat insulation layer, and carrying out vacuum packaging and curing to obtain the long-term heat-proof composite material.
Further, the hollow heat insulation layer is obtained by injecting high-temperature resin on the three-dimensional hollow fabric.
Furthermore, the three-dimensional hollow fabric is a hollow fabric formed by high-temperature resistant fibers through a special weaving mode.
Furthermore, the high-temperature resistant fiber is glass fiber, carbon fiber and quartz fiber.
Furthermore, the height of the three-dimensional hollow fabric is 2-50mm, the thickness of the surface layer is 0.2-10mm, the thickness of the core layer is 2-50mm, and the weight is 500-
Further, the high-temperature resin is phenolic resin, benzoxazine resin or polyimide resin.
In a second aspect, a long-term thermal protection composite material is prepared by the preparation method.
In a third aspect, the application of the long-term heat-proof composite material is to apply the long-term heat-proof composite material to surface heat protection of an aerospace vehicle.
The embodiment of the invention has the following beneficial effects:
compared with the existing heat-proof material, the long-term heat-proof material prepared by the method has a controllable structure, and heat-insulating layers with different thicknesses and different kinds of ablation-resistant composite material heat-proof layers can be designed according to different use environments;
the adopted hollow fabric has low fiber volume content, and more gaps exist, so that heat can be isolated more effectively;
the hollow heat-insulating layer and the surface ablation layer can adopt the same resin, so that the program matching performance between the hollow heat-insulating layer and the surface ablation layer is effectively improved.
Detailed Description
The present application is further described below with reference to examples.
In the following description, different "one embodiment" or "an embodiment" may not necessarily refer to the same embodiment, in order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art. Various embodiments may be replaced or combined, and other embodiments may be obtained according to the embodiments without creative efforts for those skilled in the art.
The invention describes a novel long-term thermal protection composite material which utilizes a three-dimensional hollow fabric as a thermal insulation layer and an ablation-resistant composite material as a surface layer. The material can isolate heat to transfer to the inside for a long time under the high temperature environment, and the heat conductivity coefficient can reach the level of the current aerogel material. The material mainly utilizes the hollow structure in the hollow fabric to isolate heat, and utilizes the erosion-resistant composite material on the surface to resist scouring and oxidation, thereby improving the heat-proof performance of the material.
A preparation method of a long-time heat-proof composite material comprises the following steps:
preparing a hollow heat insulation layer, laying ablation-resistant prepreg on the surface of the hollow heat insulation layer, and carrying out vacuum packaging and curing to obtain the long-term heat-proof composite material.
In some embodiments of the present invention, the hollow thermal insulation layer is obtained by injecting high temperature resin on a three-dimensional hollow fabric.
In some embodiments of the present invention, the three-dimensional hollow fabric is a hollow fabric formed by weaving high temperature resistant fibers in a special way.
In some embodiments of the present invention, the high temperature resistant fiber is glass fiber, carbon fiber, quartz fiber.
In some embodiments of the invention, the three-dimensional hollow fabric has a height of 2-50mm, a surface layer thickness of 0.2-10mm, a core layer thickness of 2-50mm, a weight of 500-
In some embodiments of the present invention, the high temperature resin is a phenolic resin, a benzoxazine resin, or a polyimide resin.
The long-term heat-proof composite material is prepared by the preparation method.
The application of the long-term heat-proof composite material is to apply the long-term heat-proof composite material to the surface heat protection of the aerospace craft.
Compared with the existing heat-proof material, the long-term heat-proof material prepared by the method has a controllable structure, and heat-insulating layers with different thicknesses and different kinds of ablation-resistant composite material heat-proof layers can be designed according to different use environments;
the adopted hollow fabric has low fiber volume content, and more gaps exist, so that heat can be isolated more effectively;
the hollow heat-insulating layer and the surface ablation layer can adopt the same resin, so that the program matching performance between the hollow heat-insulating layer and the surface ablation layer is effectively improved.
The three-dimensional hollow fabric is formed by weaving high-temperature resistant fibers such as glass fibers, carbon fibers, quartz fibers and the like in a special way. The hollow fabric is a novel structural fabric which is integrally woven by an upper surface layer, a lower surface layer and a core layer which is connected into a whole. The height of the hollow fabric is 2-50mm, the thickness of the surface layer is 0.2-10mm, the thickness of the core layer is 2-50mm, and the weight is 500 plus 2000 g/square meter.
And adding the hollow fabric into a proper mould, injecting high-temperature resin such as phenolic resin, benzoxazine resin, polyimide resin and the like, and curing at a proper temperature to form the hollow heat-insulating layer with certain compression strength.
After the surface of the hollow heat insulation layer is polished to be rough, ablation-resistant prepreg is laid on the surface of the hollow heat insulation layer, and the prepreg comprises high-temperature-resistant resin and high-temperature-resistant fibers. The high temperature resistant resin comprises high temperature resin such as phenolic resin, benzoxazine resin, polyimide resin and the like; the high temperature resistant fiber comprises quartz fiber, glass fiber, carbon fiber or fabric woven by the fibers.
And (3) laying the ablation-resistant prepreg to a certain number of layers, packaging and curing in a vacuum bag, wherein the curing temperature is selected according to the characteristics of the high-temperature-resistant resin.
Example 1:
the quartz fiber is woven into a hollow fabric with the thickness of 30mm, the thickness of the upper surface layer and the lower surface layer of 3mm and the stacking density of 800g/m2, and the hollow fabric is impregnated with high-temperature resistant phenolic resin and then cured for 4 hours at 160 ℃ to form the hollow heat-insulating layer. And after curing, polishing the surface of the thermal insulation layer, laying quartz fiber-phenolic resin prepreg on the surface, laying the quartz fiber-phenolic resin prepreg on the surface to 20 layers, packaging by using a vacuum bag, and curing for 4 hours at 160 ℃ by using an autoclave to form the long-term heat-proof material.
Example 2:
the quartz fiber is woven into a hollow fabric with the thickness of 20mm, the thickness of the upper surface layer and the lower surface layer of 3mm and the stacking density of 1200g/m2, and the hollow fabric is impregnated with high-temperature resistant phenolic resin and then cured for 4 hours at 160 ℃ to form the hollow heat-insulating layer. And after curing, polishing the surface of the thermal insulation layer, laying quartz fiber-phenolic resin prepreg on the surface, laying the quartz fiber-phenolic resin prepreg on the surface to 20 layers, packaging by using a vacuum bag, and curing for 4 hours at 160 ℃ by using an autoclave to form the long-term heat-proof material.
Example 3:
the quartz fiber is woven into a hollow fabric with the thickness of 30mm, the thickness of the upper surface layer and the lower surface layer of 3mm and the stacking density of 800g/m2, and the hollow fabric is impregnated with high-temperature-resistant benzoxazine and then cured for 4 hours at 180 ℃ to form a hollow heat-insulating layer. And after curing, polishing the surface of the thermal insulation layer, laying a quartz fiber-benzoxazine prepreg on the surface, laying 20 layers of the prepreg, packaging the prepreg by using a vacuum bag, and curing the prepreg for 4 hours at 180 ℃ by using an autoclave to form a long-term heat-proof material.
The performance parameters are shown in table 1:
TABLE 1
It should be noted that the above embodiments can be freely combined as necessary. The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made to the present invention by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The preparation method of the long-term heat-proof composite material is characterized by comprising the following steps:
preparing a hollow heat insulation layer, laying ablation-resistant prepreg on the surface of the hollow heat insulation layer, and carrying out vacuum packaging and curing to obtain the long-term heat-proof composite material.
2. The method for preparing long-term thermal protection composite material as claimed in claim 1, wherein the hollow thermal insulation layer is obtained by injecting high temperature resin on three-dimensional hollow fabric.
3. The method for preparing the long-term thermal protection composite material as claimed in claim 2, wherein the three-dimensional hollow fabric is a hollow fabric formed by high temperature resistant fibers through a special weaving mode.
4. The method for preparing the long-term thermal protection composite material as claimed in claim 1, wherein the high temperature resistant fiber is glass fiber, carbon fiber or quartz fiber.
5. The method for preparing the long-term heat-proof composite material as claimed in claim 2, wherein the three-dimensional hollow fabric has a height of 2-50mm, a surface layer thickness of 0.2-10mm, a core layer thickness of 2-50mm, and a weight of 500-.
6. The method for preparing the long-term heat-proof composite material as claimed in claim 2, wherein the high-temperature resin is phenolic resin, benzoxazine resin or polyimide resin.
7. A long-term thermal protection composite material, which is prepared by the preparation method according to any one of claims 1 to 6.
8. Use of a long-term thermal protection composite according to claim 7 in the surface thermal protection of aerospace vehicles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011323534.XA CN114523688A (en) | 2020-11-23 | 2020-11-23 | Long-time heat-proof composite material, preparation method and application |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011323534.XA CN114523688A (en) | 2020-11-23 | 2020-11-23 | Long-time heat-proof composite material, preparation method and application |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114523688A true CN114523688A (en) | 2022-05-24 |
Family
ID=81619494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011323534.XA Pending CN114523688A (en) | 2020-11-23 | 2020-11-23 | Long-time heat-proof composite material, preparation method and application |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114523688A (en) |
-
2020
- 2020-11-23 CN CN202011323534.XA patent/CN114523688A/en active Pending
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