CN105713389A - Material for top plates in space shuttle cabins and preparation method thereof - Google Patents
Material for top plates in space shuttle cabins and preparation method thereof Download PDFInfo
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- CN105713389A CN105713389A CN201610295902.1A CN201610295902A CN105713389A CN 105713389 A CN105713389 A CN 105713389A CN 201610295902 A CN201610295902 A CN 201610295902A CN 105713389 A CN105713389 A CN 105713389A
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- space shuttle
- ceiling panel
- inside ceiling
- panel material
- polyacrylonitrile
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L79/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing nitrogen with or without oxygen or carbon only, not provided for in groups C08L61/00 - C08L77/00
- C08L79/04—Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
- C08L79/08—Polyimides; Polyester-imides; Polyamide-imides; Polyamide acids or similar polyimide precursors
- C08L79/085—Unsaturated polyimide precursors
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/58—Measuring, controlling or regulating
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/58—Measuring, controlling or regulating
- B29C2043/5808—Measuring, controlling or regulating pressure or compressing force
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/58—Measuring, controlling or regulating
- B29C2043/5816—Measuring, controlling or regulating temperature
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L2201/00—Properties
- C08L2201/08—Stabilised against heat, light or radiation or oxydation
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L2205/00—Polymer mixtures characterised by other features
- C08L2205/03—Polymer mixtures characterised by other features containing three or more polymers in a blend
- C08L2205/035—Polymer mixtures characterised by other features containing three or more polymers in a blend containing four or more polymers in a blend
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Compositions Of Macromolecular Compounds (AREA)
Abstract
The invention discloses a material for top plates in space shuttle cabins. The material is composed of 30-40% of polyimide, 25-35% of polytetrafluoroethylene, 15-20% of polyacrylonitrile, 5-10% of polyphenyl thioether and 1-5% of rare-earth oxide. The preparation method comprises the following steps: pulverizing, mixing, relieving stress and rolling. The prepared space material has excellent mechanical strength, toughness, tensile strength and compression strength. By adding the rare-earth oxides, the heat resistance, corrosion resistance and cosmic radiation resistance of the material are enhanced. The formed crude blank is subjected to stress relieving, thereby increasing the fatigue resistance of the material.
Description
Technical field
The present invention relates to technical field of polymer materials, tool relates to a kind of space shuttle cabin inside ceiling panel material and preparation method thereof.
Background technology
Reporting according to relevant information, the quality of aerospace craft often reduces 1 kilogram, so that it may make carrier rocket alleviate 500 kilograms, and a satellite launch expense reaches several ten million dollars.The factor of high cost so that the material light weight used by the inside ceiling panel of space shuttle cabin, high-performance is particularly important.Along with developing rapidly of aerospace industry, the requirement of material is also day by day harsh, the development of one national new material and application level, embodying a national national defence and scientific research level to a great extent, therefore many countries are all placed on the development of new material and application the critical role of research work.The requirement day by day harsh in order to adapt to space industry, general purpose epoxy resin can not meet requirement, various high-performance epoxy resin is all developed being devoted in countries in the world, in order to the resin system that exploitation matches with high-performance reinforcing material (such as aramid fiber, carbon fiber etc.).But sum up, be mostly under ensureing the technological premise that epoxy resin is excellent, it is achieved epoxy resin multiple functionalized, to improve thermostability and the cementability of its solidfied material, do not comprehensively utilize and play the good characteristic of Other Engineering plastics.
Application number is 200410025427.3, the preparation method disclosing a kind of aerospace flight vehicle expanded polytetrafluoroethylsealing sealing plate material, and described preparation process includes batch mixing, preforming, pushing, calendering, dry, expanded, setting process.Use the politef sealing structure sheet material that this invention prepares, there is good chemical stability, electrical insulating property, self lubricity, overcome the cold flow properties of pure PTFE stuffing materials, will not harden or brittle and high-low temperature resistant-240 DEG C ~ 260 DEG C characteristic over time, it is adaptable to variously-shaped flat seal;But it is not its hardness and toughness are inadequate, the defensive ability/resistance ability of cosmic ray radiation is also good enough.
Application number is 200410025427.3, discloses a kind of aviation airborne equipment and heats the preparation method that can recover life size politef sheet material.Preparation process includes pretreatment, preforming, plasticizing process, process for relieving stress, Technology for Heating Processing, smooth setting process.Use the polytetrafluoroethylproducts products material that this invention obtains; there is the characteristic of good chemical stability, electrical insulating property, resistant of high or low temperature, heating restorability, resistance to aircraft fluid; suitable in aviation airborne equipment hydraulic packing system protection circle and material; but toughness is not good enough, the defensive ability/resistance ability of cosmic ray radiation is also inadequate.
Summary of the invention
This is for above technical problem and demand situation, the invention provides a kind of space shuttle cabin inside ceiling panel material and preparation method thereof, prepare mechanical strength height, good toughness, have higher tension, comprcssive strength, fatigue performance highlights, heat-resisting, corrosion-resistant, the space material of anti-cosmic ray radiation.
The present invention provides a kind of space shuttle cabin inside ceiling panel material, is made up of polyimides, politef, polyacrylonitrile, polyphenylene sulfide and rare earth oxide, and the percentage by weight of each component of material is:
Polyimides 30%-40%
Politef 25%-35%
Polyacrylonitrile 15%-20%
Polyphenylene sulfide 5%-10%
Rare earth oxide 1%-5%.
Further, the percentage by weight of each component of above-mentioned material is:
Polyimides 37%
Politef 31%
Polyacrylonitrile 19%
Polyphenylene sulfide 8%
Rare earth oxide 5%.
Further, above-mentioned polyimides is BMI.
Further, the percentage by weight of each component of above-mentioned material is:
BMI 36%
Politef 32%
Polyacrylonitrile 18%
Polyphenylene sulfide 10%
Rare earth oxide 4%
Further, above-mentioned rare earth oxide is light rare earth oxide.
Further, above-mentioned light rare earth oxide is cerium oxide.
Further, the percentage by weight of each component of above-mentioned material is:
BMI 37%
Politef 33%
Polyacrylonitrile 18%
Polyphenylene sulfide 9%
Cerium oxide 3%
The preparation method that the present invention also provides for a kind of space shuttle cabin inside ceiling panel material, preparation method is following steps:
Step S01: polyimides, politef, polyacrylonitrile, polyphenylene sulfide and rare earth oxide mixed powder are broken into the granule of 40 μm ~ 50 μm.
Step S02: under elevated pressure conditions, is warmed up to 450 DEG C ~ 500 DEG C when heating rate is 80 DEG C/h ~ 100 DEG C/h by hybrid particles, and is incubated 5 hours ~ 8 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 30 minutes ~ 40 minutes in water, to eliminate stress.
Step S04: be 40MPa ~ 50MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 250 DEG C ~ 300 DEG C when being 80 DEG C/h ~ 100 DEG C/h, then in the condition lower roll compression set type that pressure is 6MPa ~ 10MPa, through cooling, aeronautical material is obtained.
Further, in the preparation method step S02 of above-mentioned space shuttle cabin inside ceiling panel material, condition of high voltage is particularly as follows: pressure is 40MPa ~ 50MPa.
Further, in the preparation method step S04 of above-mentioned space shuttle cabin inside ceiling panel material, cooling is particularly as follows: rate of temperature fall is 80 DEG C/h ~ 100 DEG C/h.
Space shuttle cabin inside ceiling panel material prepared by the present invention, with polyimides, politef, polyacrylonitrile, polyphenylene sulfide and rare earth oxide for raw material, through preparing the space shuttle cabin inside ceiling panel material of high comprehensive performance.Polyimides 30% ~ 40%, politef 25% ~ 35%, polyacrylonitrile 15% ~ 20%, polyphenylene sulfide 5% ~ 10% ratio coordinate the mechanical strength of material, toughness, tension, comprcssive strength can be made to obtain best optimization, the addition of the rare earth oxide of 1% ~ 5%, adds the performance of material cosmic ray radiation heat-resisting, corrosion-resistant, anti-;Simultaneously after thick embryo shapes, it is not direct roll-in sizing, but through stress relief treatment 30 minutes ~ 40 minutes, adds the fatigue durability of material.
Relative to other space shuttle cabin inside ceiling panel materials, the major advantage of material of the present invention has:
1, material is under condition of equivalent thickness and quality requirements, has high specific strength, high specific stiffness, high tenacity, high damage tolerance, environmental etch anticorrosive, resistance to, it is possible to alleviate spacecraft weight.
2, prepared material can bear aerodynamic loading and possesses again multi-functional.
3, prepared material fatigue durability is good, long service life, durability and of good reliability.
Detailed description of the invention
It should be noted that when not conflicting, the embodiment in the application and the feature in embodiment can be mutually combined.The present invention is described in detail below in conjunction with embodiment.
Embodiment 1
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
BMI: 370g, politef: 330g, polyacrylonitrile: 180g, polyphenylene sulfide: 90g, cerium oxide: 30g.
Its preparation method comprises the following steps:
Step S01: BMI 370g, politef 330g, polyacrylonitrile 180g, polyphenylene sulfide 90g, cerium oxide 30g mixed powder are broken into the granule of 45 μm.
Step S02: when pressure is 45MPa, is warmed up to 450 DEG C when heating rate is 88 DEG C/h by hybrid particles, and is incubated 8 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 34 minutes in water, to eliminate stress.
Step S04: be 45MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 270 DEG C when being 89 DEG C/h, then in the condition lower roll compression set type that pressure is 8MPa, process through the cooling that rate of temperature fall is 89 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Embodiment 2
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
BMI: 360g, politef: 320g, polyacrylonitrile: 180g, polyphenylene sulfide: 100g, lanthana: 40g.
Its preparation method comprises the following steps:
Step S01: BMI 360g, politef 320g, polyacrylonitrile 180g, polyphenylene sulfide 100g, lanthana 40g mixed powder are broken into the granule of 46 μm.
Step S02: when pressure is 44MPa, is warmed up to 460 DEG C when heating rate is 86 DEG C/h by hybrid particles, and is incubated 6 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 36 minutes in water, to eliminate stress.
Step S04: be 46MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 260 DEG C when being 86 DEG C/h, then in the condition lower roll compression set type that pressure is 6MPa, process through the cooling that rate of temperature fall is 86 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Embodiment 3
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
Polyimides: 370g, politef: 310g, polyacrylonitrile: 190g, polyphenylene sulfide: 80g, holmia: 50g.
Its preparation method comprises the following steps:
Step S01: polyimides 370g, politef 310g, polyacrylonitrile 190g, polyphenylene sulfide 80g, holmia 50g mixed powder are broken into the granule of 47 μm.
Step S02: when pressure is 47MPa, is warmed up to 470 DEG C when heating rate is 87 DEG C/h by hybrid particles, and is incubated 7 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 37 minutes in water, to eliminate stress.
Step S04: be 47MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 270 DEG C when being 87 DEG C/h, then in the condition lower roll compression set type that pressure is 7MPa, process through the cooling that rate of temperature fall is 87 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Embodiment 4
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
Polyimides: 400g, politef: 350g, polyacrylonitrile: 150g, polyphenylene sulfide: 50g, Erbia: 50g.
Its preparation method comprises the following steps:
Step S01: polyimides 400g, politef 350g, polyacrylonitrile 150g, polyphenylene sulfide 50g, rare earth oxide 50g mixed powder are broken into the granule of 40 μm.
Step S02: when pressure is 40MPa, is warmed up to 450 DEG C when heating rate is 80 DEG C/h by hybrid particles, and is incubated 5 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 30 minutes in water, to eliminate stress.
Step S04: be 40MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 250 DEG C when being 80 DEG C/h, then in the condition lower roll compression set type that pressure is 6MPa, process through the cooling that rate of temperature fall is 80 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Embodiment 5
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
Polyimides: 300g, politef: 310g, polyacrylonitrile: 200g, polyphenylene sulfide: 100g, praseodymium oxide: 10g.
Its preparation method comprises the following steps:
Step S01: polyimides 300g, politef 310g, polyacrylonitrile 200g, polyphenylene sulfide 100g, praseodymium oxide 10g mixed powder are broken into the granule of 50 μm.
Step S02: when pressure is 50MPa, is warmed up to 500 DEG C when heating rate is 100 DEG C/h by hybrid particles, and is incubated 8 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 40 minutes in water, to eliminate stress.
Step S04: be 50MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 300 DEG C when being 100 DEG C/h, then in the condition lower roll compression set type that pressure is 10MPa, process through the cooling that rate of temperature fall is 100 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Embodiment 6
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
Polyimides: 400g, politef: 300g, polyacrylonitrile: 190g, polyphenylene sulfide: 70g, europium oxide: 40g.
Its preparation method comprises the following steps:
Step S01: polyimides 400g, politef 300g, polyacrylonitrile 90g, polyphenylene sulfide 70g, europium oxide 40g mixed powder are broken into the granule of 45 μm.
Step S02: when pressure is 475MPa, is warmed up to 475 DEG C when heating rate is 90 DEG C/h by hybrid particles, and is incubated 6.5 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 35 minutes in water, to eliminate stress.
Step S04: be 45MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 275 DEG C when being 90 DEG C/h, then in the condition lower roll compression set type that pressure is 8MPa, process through the cooling that rate of temperature fall is 90 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Embodiment 7
A kind of space shuttle cabin inside ceiling panel material, its raw material components includes:
Polyimides: 350g, politef: 300g, polyacrylonitrile: 175g, polyphenylene sulfide: 75g, luteium oxide: 30g.
Its preparation method comprises the following steps:
Step S01: polyimides 350g, politef 300g, polyacrylonitrile 175g, polyphenylene sulfide 75g, luteium oxide 30g mixed powder are broken into the granule of 48 μm.
Step S02: when pressure is 480MPa, is warmed up to 480 DEG C when heating rate is 95 DEG C/h by hybrid particles, and is incubated 6 hours, makes each material particles fully merge, obtains thick embryo.
Step S03: the thick embryo obtained by step S02 puts into cooling down 40 minutes in water, to eliminate stress.
Step S04: be 47MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 280 DEG C when being 85 DEG C/h, then in the condition lower roll compression set type that pressure is 7.5MPa, process through the cooling that rate of temperature fall is 95 DEG C/h, obtain space shuttle cabin inside ceiling panel material.
Experimental example 1
The embodiment of the present invention 1 ~ 7 material and common space shuttle cabin inside ceiling panel material do performance test, and performance is in Table 1.
Table 1 performance synopsis
Material | Density/kg m-3 | Compressive strength/KPa | Glass transition temperature Tg/ DEG C | Hardness/HC | Relatively corrosion-resistant degree | Relative radioprotective degree | Relative resisting fatigue degree | Comparative lifetime |
Common space shuttle cabin inside ceiling panel material | 130.0 | 400 | 285 | 70 | 1.0 | 1.0 | 1.0 | 1.0 |
Embodiment 1 material | 85.0 | 700 | 305 | 90 | 1.8 | 2.5 | 3.1 | 1.9 |
Embodiment 2 material | 87.0 | 680 | 315 | 89 | 1.9 | 2.0 | 3.0 | 2.0 |
Embodiment 3 material | 89.5 | 690 | 300 | 91 | 2.0 | 2.8 | 3.2 | 2.1 |
Embodiment 4 material | 83.0 | 710 | 325 | 92 | 1.7 | 3.0 | 3.1 | 2.2 |
Embodiment 5 material | 87.7 | 720 | 335 | 93 | 1.8 | 2.9 | 3.0 | 2.3 |
Embodiment 6 material | 85.8 | 690 | 325 | 91 | 2.0 | 3.0 | 3.2 | 2.0 |
Embodiment 7 material | 84.0 | 680 | 315 | 94 | 2.7 | 2.8 | 3.3 | 2.1 |
From above-mentioned test example, the properties of material of the present invention is above common space shuttle cabin inside ceiling panel material.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.All within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (10)
1. a space shuttle cabin inside ceiling panel material, is made up of polyimides, politef, polyacrylonitrile, polyphenylene sulfide and rare earth oxide, it is characterised in that the percentage by weight of each component of described material is:
Polyimides 30%-40%
Politef 25%-35%
Polyacrylonitrile 15%-20%
Polyphenylene sulfide 5%-10%
Rare earth oxide 1%-5%.
2. space shuttle cabin according to claim 1 inside ceiling panel material, it is characterised in that the percentage by weight of each component of described material is:
Polyimides 37%
Politef 31%
Polyacrylonitrile 19%
Polyphenylene sulfide 8%
Rare earth oxide 5%.
3. space shuttle cabin according to claim 1 inside ceiling panel material, it is characterised in that described polyimides is BMI.
4. space shuttle cabin according to claim 1 inside ceiling panel material, it is characterised in that the percentage by weight of each component of described material is:
BMI 36%
Politef 32%
Polyacrylonitrile 18%
Polyphenylene sulfide 10%
Rare earth oxide 4%.
5. space shuttle cabin according to claim 1 inside ceiling panel material, it is characterised in that described rare earth oxide is light rare earth oxide.
6. space shuttle cabin according to claim 1 inside ceiling panel material, it is characterised in that described light rare earth oxide is cerium oxide.
7. space shuttle cabin according to claim 1 inside ceiling panel material, it is characterised in that the percentage by weight of each component of described material is:
BMI 37%
Politef 33%
Polyacrylonitrile 18%
Polyphenylene sulfide 9%
Cerium oxide 3%.
8. the preparation method of a space shuttle cabin as claimed in claim 1 inside ceiling panel material, it is characterised in that preparation method comprises the following steps:
Step S01: polyimides, politef, polyacrylonitrile, polyphenylene sulfide and rare earth oxide mixed powder are broken into the granule of 40 μm ~ 50 μm;
Step S02: under elevated pressure conditions, is warmed up to 450 DEG C ~ 500 DEG C when heating rate is 80 DEG C/h ~ 100 DEG C/h by hybrid particles, and is incubated 5 hours ~ 8 hours, makes each material particles fully merge, obtains thick embryo;
Step S03: the thick embryo obtained by step S02 puts into cooling down 30 minutes ~ 40 minutes in water, to eliminate stress;
Step S04: be 40MPa ~ 50MPa at pressure by eliminating the thick embryo after stress, heating rate is warmed up to 250 DEG C ~ 300 DEG C when being 80 DEG C/h ~ 100 DEG C/h, then in the condition lower roll compression set type that pressure is 6MPa ~ 10MPa, through cooling, aeronautical material is obtained.
9. the preparation method of space shuttle cabin according to claim 8 inside ceiling panel material, it is characterised in that described step S02 mesohigh condition is particularly as follows: pressure is 40MPa ~ 50MPa.
10. the preparation method of space shuttle cabin according to claim 8 inside ceiling panel material, it is characterised in that in described step S04, cooling is particularly as follows: rate of temperature fall is 80 DEG C/h ~ 100 DEG C/h.
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109705576A (en) * | 2018-12-27 | 2019-05-03 | 中广核高新核材科技(苏州)有限公司 | A kind of wear-resistant self-lubricating thermoplastic polyimide composite material and preparation method thereof |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101864170A (en) * | 2009-04-17 | 2010-10-20 | 爱尔铃克铃尔股份公司 | Polymer complex and the structural part that under the situation of using this mixture, prepares |
-
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101864170A (en) * | 2009-04-17 | 2010-10-20 | 爱尔铃克铃尔股份公司 | Polymer complex and the structural part that under the situation of using this mixture, prepares |
Non-Patent Citations (1)
Title |
---|
陈涛等: "稀土化合物对PTFE基三层复合材料摩檫磨损性能的影响", 《润滑与密封》 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109705576A (en) * | 2018-12-27 | 2019-05-03 | 中广核高新核材科技(苏州)有限公司 | A kind of wear-resistant self-lubricating thermoplastic polyimide composite material and preparation method thereof |
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Application publication date: 20160629 |