CN115304814A - Light composite material heat insulation tile for aerospace and manufacturing method thereof - Google Patents
Light composite material heat insulation tile for aerospace and manufacturing method thereof Download PDFInfo
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- CN115304814A CN115304814A CN202211076340.3A CN202211076340A CN115304814A CN 115304814 A CN115304814 A CN 115304814A CN 202211076340 A CN202211076340 A CN 202211076340A CN 115304814 A CN115304814 A CN 115304814A
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- heat insulation
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- 239000002131 composite material Substances 0.000 title claims abstract description 43
- 238000009413 insulation Methods 0.000 title claims abstract description 30
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 22
- 239000004917 carbon fiber Substances 0.000 claims abstract description 22
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000000463 material Substances 0.000 claims abstract description 21
- 239000000758 substrate Substances 0.000 claims abstract description 18
- 238000005728 strengthening Methods 0.000 claims abstract description 15
- 230000005855 radiation Effects 0.000 claims abstract description 13
- 238000002679 ablation Methods 0.000 claims abstract description 12
- 239000000919 ceramic Substances 0.000 claims abstract description 6
- 238000005507 spraying Methods 0.000 claims description 33
- 238000000576 coating method Methods 0.000 claims description 17
- 239000011248 coating agent Substances 0.000 claims description 14
- 238000010276 construction Methods 0.000 claims description 7
- 230000002708 enhancing effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 5
- 238000004140 cleaning Methods 0.000 claims description 3
- 239000000428 dust Substances 0.000 claims description 3
- 239000004519 grease Substances 0.000 claims description 3
- 239000012756 surface treatment agent Substances 0.000 claims description 3
- 239000003973 paint Substances 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000012720 thermal barrier coating Substances 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J7/00—Chemical treatment or coating of shaped articles made of macromolecular substances
- C08J7/04—Coating
- C08J7/05—Forming flame retardant coatings or fire resistant coatings
-
- 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
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- Health & Medical Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Medicinal Chemistry (AREA)
- Thermal Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention relates to a light composite material heat insulation tile for spaceflight, which structurally comprises four layers of materials, wherein the four layers of materials are sequentially arranged from the joint with the surface of a spacecraft: the carbon fiber composite material comprises a carbon fiber composite material substrate layer, a heat insulation layer, a ceramic ablation layer and a surface mechanical property strengthening and infrared radiation function strengthening material layer. The manufacturing process is simple, the material cost is low, the used carbon fiber composite material substrate can be recycled, and the thermal protection cost of the commercial spacecraft can be greatly reduced.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to a light composite material heat insulation tile for spaceflight and a manufacturing method thereof.
Background
With the development of commercial aerospace technology, reusable launch vehicles and multiple reentry spacecraft have gradually become one of the main directions of aerospace technology development in recent years. Unlike the single-use rocket and spacecraft, the reusable device requires the surface heat-insulating layer to be replaced and maintained conveniently. However, the conventional surface heat-proof and heat-insulating layer is difficult to peel off from the surface of the spacecraft, and the detachment process is also very easy to damage the metal surface below and even generate destructive deformation. To address such problems, the aerospace industry is currently attempting to use two types of solutions: firstly, an ablation-resistant heat-insulating layer is used, namely the surface heat-insulating layer can be repeatedly used for a plurality of times without replacement; secondly, the design of using the heat-proof tile which is easy to replace. The main problem with the first type of solution is that a relatively thick initial refractory layer is required, which requires additional mass to be carried for each shot. The main problem with the second category of solutions is the requirement for a reliable mounting, especially for locations where the contour is relatively complex. At present, the two schemes have scenes suitable for application in the aerospace industry, so that the two schemes have development necessity.
The Chinese patent application with the application number of CN200910017754.7 provides a method for manufacturing a spacecraft heat insulation tile, and the materials of the spacecraft heat insulation tile are sintered quartz glass fibers and fillers. The problem is mainly that the density of the material is large, generally exceeding 3.0g/cm 3 It is not easy to replace and has poor heat insulation performance.
Therefore, the development of a lighter, high-strength, high-temperature resistant, easily replaceable and low-cost heat insulation tile still has great technical significance.
Disclosure of Invention
The invention provides a light composite material heat insulation tile for spaceflight and a manufacturing method thereof, aiming at solving the problems in the prior art.
The invention relates to a light composite material heat insulation tile for spaceflight, which structurally comprises four layers of materials, wherein the four layers of materials are sequentially arranged from the joint with the surface of a spacecraft: the carbon fiber composite material comprises a carbon fiber composite material substrate layer, a heat insulation layer, a ceramizable ablation layer and a surface mechanical property strengthening and infrared radiation function strengthening material layer. The structure schematic diagram is shown in fig. 1.
In some embodiments of the invention, the carbon fiber composite substrate layer is a carbon fiber composite.
In some embodiments of the invention, the thermal barrier layer is an SR107-TI thermal barrier coating.
In some embodiments of the invention, the ceramifiable ablative layer is a SR107-TA ablative coating.
In some embodiments of the present invention, the surface mechanical property enhancing and infrared radiation function enhancing material layer is SR107-TR radiation enhanced paint.
A method for manufacturing a light composite material heat insulation tile for spaceflight comprises the following steps:
1) Cleaning the surface of the carbon fiber composite material substrate layer, removing grease, burrs and dust, and then spraying a surface promoter on the construction surface;
2) Spraying a heat insulation layer on the construction surface of the carbon fiber composite material substrate layer, wherein the thickness of single spraying is not more than 0.3mm, and repeatedly spraying until the preset thickness is reached;
3) Continuously spraying a ceramic ablation layer on the dried spraying heat-insulating layer, wherein the thickness of single spraying is not more than 0.2mm, and repeatedly spraying until the preset thickness is reached;
4) Continuously spraying a surface mechanical property strengthening and infrared radiation function strengthening material layer on the dried ceramizable ablation layer, wherein the single spraying thickness is not more than 0.2mm, and repeatedly spraying until the preset thickness is reached;
5) And after all the coatings are dried, checking the thickness of each layer and the overall size of the workpiece to obtain a finished product.
In some embodiments of the invention, the surface promoter is a han-gol-tai 7455 colorless transparent surface treatment agent.
Compared with the prior art, the light composite material heat insulation tile for spaceflight, which is manufactured by the invention, mainly has the following advantages:
1) By using the carbon fiber composite material substrate, the heat insulation tile can be quickly assembled and disassembled by using a mortise and tenon structure;
2) The light composite material heat insulation tile for spaceflight is manufactured by using the composite heat insulation preventing coating, a mould is not needed in the manufacturing process, only spraying construction is needed to be carried out on a customized substrate, the production efficiency is high, and the cost is low; meanwhile, flexible manufacturing can be realized, and coating structures on individual workpieces can be customized according to different requirements of the surface of the spacecraft;
3) The existing rocket thermal-shock-resistant coating is superior to the existing composite ceramic thermal-shock-resistant tile in cost and performance.
The thermal insulation tile of the present invention allows for increased thermal insulation protection of the reusable spacecraft surface to the level of single use spacecraft at similar cost and with the possibility of using continuously improved formulations. The manufacturing process is simple, the material cost is low, the used carbon fiber composite material substrate can be recycled, and the thermal protection cost of the commercial spacecraft can be greatly reduced; meanwhile, the material system and the process route of the invention can also be used for producing the thermal protection material of a new energy battery system.
Drawings
Fig. 1 is a schematic structural view of the aerospace lightweight composite material heat insulation tile.
Wherein, 1 is a carbon fiber composite material substrate layer, 2 is a heat insulation layer, 3 is a ceramic ablation layer, and 4 is a surface mechanical property strengthening and infrared radiation function strengthening material layer.
Fig. 2 is a schematic view showing a structure of a semi-cylindrical insulating tile according to example 1.
Detailed Description
In order to better understand the present invention, the following examples are further provided to illustrate the content of the present invention, but the present invention is not limited to the following examples.
Carbon fiber composite material: purchased from keteis (china) composite, llc.
SR107-TI heat insulation coating, SR107-TA ablation coating and SR107-TR radiation strengthening coating are all produced by Zhoushan aerospace New Material Co.
Hangaoletai 7455 colorless transparent surface treatment agent: produced by loctite belonging to Hangao (China) investment Limited.
Example 1
In order to protect the surface of a specific reentrant spacecraft, it is necessary to manufacture a half-cylindrical insulating tile as shown in fig. 2, with the protection direction facing outwards. According to the design scheme, the thickness of the heat insulation layer is 2.2mm, the thickness of the ablation layer is 2.0mm, and the thickness of the radiation strengthening layer is 1.5mm.
The manufacturing process is as follows:
1) Performing three-dimensional mapping detection on a carbon fiber composite material substrate, cleaning the surface after the substrate is qualified, removing grease, burrs and dust, and spraying a colorless and transparent surface treating agent of Han Gao Tai 7455 on a construction surface for surface pretreatment;
2) Spraying SR107-TI heat insulation coating on the construction surface of the carbon fiber composite material substrate, wherein the thickness of single spraying is not more than 0.3mm, and repeatedly spraying until the thickness reaches 2.2mm;
3) Continuously spraying SR107-TA ablation coating on the dried SR107-TI coating, wherein the thickness of single spraying is not more than 0.2mm, and repeatedly spraying until the thickness reaches 2.0;
4) Continuously spraying SR107-TR radiation strengthening coating on the dried SR107-TA coating, wherein the thickness of single spraying is not more than 0.2mm, and repeatedly spraying until the thickness reaches 1.5mm;
5) In order to measure the thickness of each layer conveniently, a lining plate is pasted beside the carbon fiber material composite substrate, after all coatings are dried, the thickness of each layer of the lining plate is cut and checked, and the size of the whole workpiece is measured and qualified.
The basic properties of the prepared insulation tile are shown in table 1 below.
TABLE 1
The above description is only one embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be able to substitute or change the technical solution of the present invention and the inventive concept thereof within the technical scope of the present invention.
Claims (7)
1. The light composite material heat insulation tile for the spaceflight is characterized by comprising four layers of materials, wherein the materials are sequentially from the joint with the surface of a spacecraft: the carbon fiber composite material comprises a carbon fiber composite material substrate layer, a heat insulation layer, a ceramizable ablation layer and a surface mechanical property strengthening and infrared radiation function strengthening material layer.
2. The lightweight composite thermal insulating tile for aerospace as claimed in claim 1, wherein the carbon fiber composite substrate layer is a carbon fiber composite.
3. The lightweight composite thermal insulating tile for aerospace as claimed in claim 1, wherein the thermal insulating layer is SR107-TI thermal insulating coating.
4. The lightweight composite thermal insulating tile for aerospace as claimed in claim 1, wherein said ceramifiable ablative layer is SR107-TA ablative coating.
5. The lightweight composite thermal insulating tile for aerospace as claimed in claim 1, wherein the surface mechanical property enhancing and infrared radiation function enhancing material layer is SR107-TR radiation enhancing paint.
6. A method of manufacturing an aerospace lightweight composite thermal insulating tile as claimed in claim 1, comprising the steps of:
1) Cleaning the surface of the carbon fiber composite material substrate layer, removing grease, burrs and dust, and then spraying a surface promoter on the construction surface;
2) Spraying a heat insulation layer on the construction surface of the carbon fiber composite material substrate layer, wherein the thickness of single spraying is not more than 0.3mm, and repeatedly spraying until the preset thickness is reached;
3) Continuously spraying a ceramic ablation layer on the dried spraying heat-insulating layer, wherein the thickness of single spraying is not more than 0.2mm, and repeatedly spraying until the preset thickness is reached;
4) Continuously spraying a surface mechanical property strengthening and infrared radiation function strengthening material layer on the dried ceramic ablation layer, wherein the thickness of single spraying is not more than 0.2mm, and repeatedly spraying until the preset thickness is reached;
5) And after all the coatings are dried, checking the thickness of each layer and the overall size of the workpiece to obtain a finished product.
7. The method for manufacturing the light composite material heat insulation tile for spaceflight as claimed in claim 6, wherein the surface promoter is han gao le tai 7455 colorless transparent surface treatment agent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211076340.3A CN115304814A (en) | 2022-09-05 | 2022-09-05 | Light composite material heat insulation tile for aerospace and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211076340.3A CN115304814A (en) | 2022-09-05 | 2022-09-05 | Light composite material heat insulation tile for aerospace and manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115304814A true CN115304814A (en) | 2022-11-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211076340.3A Pending CN115304814A (en) | 2022-09-05 | 2022-09-05 | Light composite material heat insulation tile for aerospace and manufacturing method thereof |
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| Country | Link |
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| CN (1) | CN115304814A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060118992A1 (en) * | 2004-12-03 | 2006-06-08 | Geng-Wen Chang | Process of maniudacturing dual-layered thermal insulation composite panel |
| CN103727358A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal insulation material structure capable of reaching low temperature |
| CN105924184A (en) * | 2016-04-20 | 2016-09-07 | 浙江大学 | High-temperature infrared radiant coating used for industrial furnace and preparation method thereof |
| CN113773692A (en) * | 2021-09-28 | 2021-12-10 | 舟山腾宇航天新材料有限公司 | Unidirectional fiber reinforced aerospace-grade heat-insulation-preventing coating material |
-
2022
- 2022-09-05 CN CN202211076340.3A patent/CN115304814A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060118992A1 (en) * | 2004-12-03 | 2006-06-08 | Geng-Wen Chang | Process of maniudacturing dual-layered thermal insulation composite panel |
| CN103727358A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal insulation material structure capable of reaching low temperature |
| CN105924184A (en) * | 2016-04-20 | 2016-09-07 | 浙江大学 | High-temperature infrared radiant coating used for industrial furnace and preparation method thereof |
| CN113773692A (en) * | 2021-09-28 | 2021-12-10 | 舟山腾宇航天新材料有限公司 | Unidirectional fiber reinforced aerospace-grade heat-insulation-preventing coating material |
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Application publication date: 20221108 |
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| RJ01 | Rejection of invention patent application after publication |