CN106978729A - A kind of high temperature resistant aerospace composite - Google Patents
A kind of high temperature resistant aerospace composite Download PDFInfo
- Publication number
- CN106978729A CN106978729A CN201710172137.9A CN201710172137A CN106978729A CN 106978729 A CN106978729 A CN 106978729A CN 201710172137 A CN201710172137 A CN 201710172137A CN 106978729 A CN106978729 A CN 106978729A
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- CN
- China
- Prior art keywords
- temperature resistant
- carbon fiber
- high temperature
- aerospace composite
- resistant aerospace
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
- D06M15/00—Treating fibres, threads, yarns, fabrics, or fibrous goods made from such materials, with macromolecular compounds; Such treatment combined with mechanical treatment
- D06M15/19—Treating fibres, threads, yarns, fabrics, or fibrous goods made from such materials, with macromolecular compounds; Such treatment combined with mechanical treatment with synthetic macromolecular compounds
- D06M15/37—Macromolecular compounds obtained otherwise than by reactions only involving carbon-to-carbon unsaturated bonds
- D06M15/59—Polyamides; Polyimides
-
- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
- D06M2101/00—Chemical constitution of the fibres, threads, yarns, fabrics or fibrous goods made from such materials, to be treated
- D06M2101/40—Fibres of carbon
-
- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
- D06M2200/00—Functionality of the treatment composition and/or properties imparted to the textile material
- D06M2200/25—Resistance to light or sun, i.e. protection of the textile itself as well as UV shielding materials or treatment compositions therefor; Anti-yellowing treatments
-
- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
- D06M2200/00—Functionality of the treatment composition and/or properties imparted to the textile material
- D06M2200/30—Flame or heat resistance, fire retardancy properties
Abstract
The embodiment of the invention discloses a kind of high temperature resistant aerospace composite, described high temperature resistant aerospace composite is clad structure, described clad structure includes carbon fiber sandwich layer and polyimides outer layer, and described polyimides external sheath is on described carbon fiber sandwich layer；High temperature resistant aerospace composite provided in an embodiment of the present invention; the rope used in particular circumstances, net and the textile fabric composite for weaving fabric can be used as; while carbon fiber premium properties is ensured; the significant performance for improving heat resistance and uvioresistant, anti-cosmic ray and space high energy particle; the fields such as Aero-Space, petrochemical industry and power industry can be widely used in, with good protective value and protective action.
Description
Technical field
The present invention relates to technical field of composite materials, more particularly to a kind of high temperature resistant aerospace composite.
Background technology
Carbon fiber (carbon fiber, abbreviation CF) material, is a kind of high intensity of phosphorus content more than 95%, high-modulus
The new fiber materials of fiber.It is to be piled up to form along fiber axial direction by organic fibers such as flake graphites, through carbonization
And microcrystalline graphite material obtained from graphitization processing.Carbon fiber " soft outside but hard inside ", quality is lighter than metallic aluminium, but intensity is higher than
Steel, and be all important materials in defence and military and civilian aspect with corrosion-resistant, high-modulus characteristic.It not only has
The intrinsic intrinsic property of carbon material, has both the soft machinability of textile fabric again, is reinforcing fiber of new generation.
Carbon fiber has many premium properties, and the axial strength and modulus of carbon fiber are high, and density is low, higher than performance, without compacted
Become, superhigh temperature resistant under non-oxidizing atmosphere, fatigue durability is good, specific heat and electric conductivity between nonmetallic between metal, thermal expansion system
Number is small and with anisotropy, and good corrosion resistance, X-ray transparent is good.Good electrical and thermal conductivity performance, electromagnetic wave shielding are good
Deng.Carbon fiber is compared with traditional glass fibre, and Young's modulus is it more than 3 times；It is compared with Kafra fiber, and Young's modulus is
Its 2 times or so, the insoluble and in-expandable in organic solvent, acid, alkali, corrosion resistance is protruded.
In aerospace field, although carbon fibre material has preferable mechanical property and heat resistance, carbon fiber
Under ultraviolet light or ray space, the effect irradiation of high energy particle, decline by a relatively large margin occurs in the mechanical property of fiber, this
Greatly influence or limit application of the carbon fiber in advanced field of compound material.Therefore, how to have produced anti-high energy grain
The carbon fibre composite of sub- ray turns into the key issue that letter need to be solved.
The content of the invention
The purpose of the embodiment of the present invention is to provide a kind of high temperature resistant aerospace composite, to reach high temperature resistant, anti-high energy
The purpose of particle ray.
To reach above-mentioned purpose, the embodiment of the invention discloses a kind of high temperature resistant aerospace composite, described high temperature resistant
Aerospace composite is clad structure, and described clad structure includes carbon fiber sandwich layer and polyimides outer layer, described polyamides
Imines external sheath is on described carbon fiber sandwich layer.
Optionally, described carbon fiber is：
Polyacrylonitrile-based carbon fibre, asphalt base carbon fiber, viscose-based carbon fiber, phenolic aldehyde base carbon fibre and vapor grown carbon
One kind of fiber.
Optionally, the Denier range of described carbon fiber is：15~20D.
Optionally, the fiber number of described carbon fiber is：19D.
Optionally, described high-temperature resistant anti-ultraviolet composite fiber material is a diameter of：0.1~2.5mm.
Optionally, described carbon fiber sandwich layer and polyimides outer layer are coaxial.
High temperature resistant aerospace composite provided in an embodiment of the present invention, can be used as the rope, net used in particular circumstances
And the textile fabric composite of weaving fabric, while carbon fiber premium properties is ensured, significantly improve heat resistance
Can and uvioresistant, anti-cosmic ray and space high energy particle performance, can be widely used in Aero-Space, petrochemical industry with
And the field such as power industry, with good protective value and protective action.Also, it is fine in carbon using polyimides external sheath
Tie up on sandwich layer, in space industry, can play and its significant high temperature resistant, the effect of anti-high energy particle ray.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation of high temperature resistant aerospace composite provided in an embodiment of the present invention.
Embodiment
Embodiments of the invention are elaborated below, the present embodiment is carried out lower premised on technical solution of the present invention
Implement, give detailed embodiment and specific operating process, but protection scope of the present invention is not limited to following implementations
Example.
Fig. 1 is a kind of structural representation of high temperature resistant aerospace composite provided in an embodiment of the present invention, described resistance to height
Warm aerospace composite is clad structure, and described clad structure includes carbon fiber sandwich layer 1 and polyimides outer layer 2, described
Polyimides outer layer 2 is coated on described carbon fiber sandwich layer 1.
Specifically, described carbon fiber is：Polyacrylonitrile-based carbon fibre, asphalt base carbon fiber, viscose-based carbon fiber, phenolic aldehyde
One kind of base carbon fibre and gas-phase growth of carbon fibre.
Specifically, the Denier range of described carbon fiber is：15~20D.
Specifically, the fiber number of described carbon fiber is：19D.
Specifically, described high-temperature resistant anti-ultraviolet composite fiber material is a diameter of：0.1~2.5mm.
Specifically, described carbon fiber sandwich layer and polyimides outer layer is coaxial.
It should be noted that the preparation of high temperature resistant aerospace composite can be：By the polyimides and carbon fiber of preparation
Extrusion cladding is carried out with twin-screw, extrusion temperature is controlled at 175 DEG C or so, obtain different thick by changing the Denier range of synnema
Thin high temperature resistant space flight complex fiber material.By adding a tensometer and to the micro- of cored template before synnema enters spinneret template
Transfer control composite fibre concentricity, polyimides is uniformly coated on carbon fiber.
It can be seen that, high temperature resistant aerospace composite provided in an embodiment of the present invention can be as using in particular circumstances
Rope, net and the textile fabric composite for weaving fabric, while carbon fiber premium properties is ensured, are significantly improved resistance to
The performance of hot property and uvioresistant, anti-cosmic ray and space high energy particle, can be widely used in Aero-Space, oil
The field such as work and power industry, with good protective value and protective action.Also, existed using polyimides external sheath
On carbon fiber sandwich layer, in space industry, it can play and its significant high temperature resistant, the effect of anti-high energy particle ray.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
Any modifications, equivalent substitutions and improvements made within refreshing and principle etc., should be included in the scope of the protection.
Claims (6)
1. a kind of high temperature resistant aerospace composite, it is characterised in that：Described high temperature resistant aerospace composite is clad structure, institute
The clad structure stated includes carbon fiber sandwich layer and polyimides outer layer, and described polyimides external sheath is in described carbon fiber
On sandwich layer.
2. a kind of high temperature resistant aerospace composite according to claim 1, it is characterised in that：Described carbon fiber is：
Polyacrylonitrile-based carbon fibre, asphalt base carbon fiber, viscose-based carbon fiber, phenolic aldehyde base carbon fibre and gas-phase growth of carbon fibre
One kind.
3. a kind of high temperature resistant aerospace composite according to claim 1, it is characterised in that：The fiber number of described carbon fiber
Scope is：15~20D.
4. a kind of high temperature resistant aerospace composite according to claim 1, it is characterised in that：The fiber number of described carbon fiber
For：19D.
5. a kind of high temperature resistant aerospace composite according to claim 1, it is characterised in that：Described high-temperature resistant anti-ultraviolet
Composite fibre it is a diameter of：0.1~2.5mm.
6. a kind of high temperature resistant aerospace composite according to claim 1, it is characterised in that：Described carbon fiber sandwich layer and
Polyimides outer layer is coaxial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710172137.9A CN106978729A (en) | 2017-03-22 | 2017-03-22 | A kind of high temperature resistant aerospace composite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710172137.9A CN106978729A (en) | 2017-03-22 | 2017-03-22 | A kind of high temperature resistant aerospace composite |
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| Publication Number | Publication Date |
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| CN106978729A true CN106978729A (en) | 2017-07-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710172137.9A Pending CN106978729A (en) | 2017-03-22 | 2017-03-22 | A kind of high temperature resistant aerospace composite |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109797469A (en) * | 2019-02-19 | 2019-05-24 | 南京中奥航天应用技术研究院(有限合伙) | The immune enhanced carbon fiber of radiation protection of raising and its fabric braiding structure are taken in aerospace |
| CN113801322A (en) * | 2021-10-01 | 2021-12-17 | 武汉纺织大学 | Soluble high-transparency polyimide, polyimide coated fabric and preparation method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103483816A (en) * | 2013-07-31 | 2014-01-01 | 宁波泛龙塑料新材料有限公司 | Carbon fiber reinforced polyimide composite material and preparation method thereof |
| CN104271646A (en) * | 2012-03-28 | 2015-01-07 | 东丽碳纤维美国股份有限公司 | Thermoplastic molding preform |
| CN104629363A (en) * | 2013-11-11 | 2015-05-20 | 黑龙江鑫达企业集团有限公司 | Preparation of aircraft engine circumference polyimides high temperature resistance composite material |
| CN104629365A (en) * | 2015-02-17 | 2015-05-20 | 哈尔滨工程大学 | Method for preparing carbon fiber-polyimide composite material |
-
2017
- 2017-03-22 CN CN201710172137.9A patent/CN106978729A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104271646A (en) * | 2012-03-28 | 2015-01-07 | 东丽碳纤维美国股份有限公司 | Thermoplastic molding preform |
| CN103483816A (en) * | 2013-07-31 | 2014-01-01 | 宁波泛龙塑料新材料有限公司 | Carbon fiber reinforced polyimide composite material and preparation method thereof |
| CN104629363A (en) * | 2013-11-11 | 2015-05-20 | 黑龙江鑫达企业集团有限公司 | Preparation of aircraft engine circumference polyimides high temperature resistance composite material |
| CN104629365A (en) * | 2015-02-17 | 2015-05-20 | 哈尔滨工程大学 | Method for preparing carbon fiber-polyimide composite material |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109797469A (en) * | 2019-02-19 | 2019-05-24 | 南京中奥航天应用技术研究院(有限合伙) | The immune enhanced carbon fiber of radiation protection of raising and its fabric braiding structure are taken in aerospace |
| CN113801322A (en) * | 2021-10-01 | 2021-12-17 | 武汉纺织大学 | Soluble high-transparency polyimide, polyimide coated fabric and preparation method |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20181218 Address after: 230000 Room 201, 3 Yikang Garden Building, Shengli Road, Yaohai District, Hefei City, Anhui Province Applicant after: Hefei Fuward Enterprise Management Consulting Co., Ltd. Address before: 230000 Room 209, 210, 213, 214, Electronic Building, No. 2 Tianda Road, Hefei High-tech Zone, Shushan District, Hefei City, Anhui Province Applicant before: Anhui Bonding Technology Co., Ltd. |
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Application publication date: 20170725 |