CN103909691A - Carbon-fiber needled preformed body with gradiently-changed body density - Google Patents
Carbon-fiber needled preformed body with gradiently-changed body density Download PDFInfo
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Abstract
The invention discloses a carbon-fiber needled preformed body with gradiently-changed body density. The preformed body is formed by continuously needling three layers of carbon-fiber needled preformed bodies in a multi-angle and layer-by-layer crossed manner, wherein the density of the preformed body at a middle layer is larger than the densities of the preformed bodies at an upper layer and a lower layer, and each preformed body is formed by compositing a layer of weftless carbon cloth paved in a 0-degree/90-degree angle with a layer of mesh tire and continuously needling in the layer-by-layer manner. The preformed body has the advantages of short preparation cycle and low production cost in carbon/carbon sedimentation technological process, and a carbon/carbon composite material produced from the preformed body has excellent performances of wear resistance, high temperature resistance, low expansion coefficient, high heat conductivity, good heat shock resistance, light weight and the like. The high-performance carbon-fiber needled preformed body is a novel functional composite structure product and has wide application prospects in the fields of aviation, space flight, civil construction, military and the like due to the specific structure and advanced production process.
Description
Affiliated technical field
The present invention relates to a kind of preparation method of felt body, particularly relate to a kind of carbon fiber needling preform of volume density graded.
Background technology
High-performance carbon fibre needling preform, after carbon/carbon depositing operation of high-tech is processed, having the performances such as rub resistance, high temperature resistant, quality is light, is the emerging high-tech new material of modern development, is the widely used new materials in field such as Aero-Space, traffic, military people.
The original structure of carbon fabric perform is to adopt carbon fiber-free weft fabric and carbon fibre web tire to make the precast body of the permanent density of density through multilayer acupuncture.Processing step mainly comprises: be 1. 40-600g/m by producing to staple card Cheng Houwei 1-2mm, the surface density of 50-60
2net tire: 2. by compound to net tire and carbon fiber, and continuous needle becomes three-dimensional precast body.
In the depositing operations such as follow-up high temperature cabonization, graphitization, there is the easily problem of sealing of precast body surface pore in above-mentioned original carbon fiber needling preform, for guaranteeing high density and the uniformity of product, can only promote osmosis by low temperature, low-flow concentration, cause the densified cycle very long, production cost is very high.
Summary of the invention
The present invention is in order to overcome above-mentioned technical deficiency, provide the outer density of a kind of internal layer density ratio high carbon fiber needling preform, this carbon fiber needling preform is conducive to reacting gas and deposits from the inside to the outside in precast body inside in subsequent deposition process, can effectively solve the easily problem of sealing of precast body surface pore, high density and the uniformity of product are not only guaranteed, and greatly shortened manufacturing cycle, thereby significantly reduce production cost.
Carbon fiber needling preform of the present invention, this precast body successively intersects continuous needle by three layers of carbon fiber needling preform multi-angle and forms, wherein the bilevel density of the density ratio of intermediate layer precast body is large, each layer of precast body is compound without latitude carbon cloth and one deck net tire by 0 ° of one deck/90 ° of layings, and successively continuous needle forms.
Above-mentioned carbon fiber needling preform thickness in monolayer is 5-50mm, carbon fiber needling preform individual layer interlayer density is 16 ± 1 layers/cm, levels carbon fiber needling preform bulk density is 0.25-0.5, intermediate layer carbon fiber needling preform bulk density is 0.5-0.75, and needling density is 40-45 pin/cm
3.
The present invention adopts carbon fiber-free weft fabric and carbon fibre web tire to prepare high-performance carbon fibre needling preform, and density ratio outer density in precast body middle level is high.In subsequent deposition process, use this precast body to save 20% left and right than old technology production cost, not only saved human and material resources, and greatly shortened the production cycle.
The specific embodiment
As shown in Figure 1, carbon fiber needling preform of the present invention, this precast body successively intersects continuous needle by three layers of carbon fiber needling preform multi-angle and forms, wherein the bilevel density of the density ratio of intermediate layer precast body is large, each layer of precast body is compound without latitude carbon cloth and one deck net tire by 0 ° of one deck/90 ° of layings, and successively continuous needle forms.Precast body thickness in monolayer is 5-50mm, and carbon fiber needling preform individual layer interlayer density is 16 ± 1 layers/cm, and levels carbon fiber needling preform bulk density is 0.25-0.5, and intermediate layer carbon fiber needling preform bulk density is 0.5-0.75.
The preparation method of composite needling preform, mainly comprises the following steps:
1) carbon fiber being cut into length is 38-48mm, and density 30-38g/m
2short fiber, spray water makes short fiber keep 3-5% humidity, puts into afterwards baking oven and is heated to 30 degrees Celsius, insulation 28-30 hour, forms separation of material through opener shredding after taking out short fiber, then the short fiber after separating is laid to net tire.
2) carbon fiber long array is become 0 °/90 ° of layings without latitude carbon cloth, compound and successively carry out continuous needle and form individual layer composite with net tire, thickness in monolayer is controlled at 5-50mm.
3) take step 2) the individual layer composite prepared is the elementary cell of product, by compound 3-layer composite material and through multi-angle successively intersect continuous needle form composite pricking prefabricated body, controlling levels carbon fiber needling preform bulk density is 0.25-0.5, intermediate layer carbon fiber needling preform bulk density is 0.5-0.75, interlayer density is 16 ± 1 layers/cm, and stinging in advance density is 40-45 pin/cm
3depth of needle is 15-150mm.
The present invention adopts carbon fibre web tire to be of value to the intensity that improves precast body interlayer structure.Make precast body levels integrated by intersection acupuncture, guarantee that in carbon/carbon depositing operation, carburizing rate is high, even structure.Compared with the needling preform of this carbon fiber needling preform and density constant, because of precast body density increase from outside to inside, outer hole is large compared with internal layer, in subsequent deposition process, being conducive to reacting gas deposits from the inside to the outside in precast body inside, can effectively solve the easily problem of sealing of precast body surface pore, use this precast body to save 20% left and right than old technology production cost, not only saved human and material resources, and greatly shortened the production cycle.Guaranteeing under the prerequisite of product quality, price and external like product have competitiveness.
Claims (3)
1. a carbon fiber needling preform, this precast body successively intersects continuous needle by three layers of carbon fiber needling preform multi-angle and forms, and it is characterized in that: the bilevel density of density ratio of intermediate layer precast body is large.
2. carbon fiber needling preform according to claim 1, is characterized in that: each layer of precast body is compound without latitude carbon cloth and one deck net tire by 0 ° of one deck/90 ° of layings, and successively continuous needle forms.
3. carbon fiber needling preform according to claim 1 and 2, it is characterized in that: carbon fiber needling preform thickness in monolayer is 5-50mm, carbon fiber needling preform individual layer interlayer density is 16 ± 1 layers/cm, levels carbon fiber needling preform bulk density is 0.25-0.5, and intermediate layer carbon fiber needling preform bulk density is 0.5-0.75.
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| CN103909691B CN103909691B (en) | 2017-04-12 |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691338A (en) * | 2014-12-20 | 2015-06-10 | 中南大学 | Producing method of copper wire mesh modified carbon/carbon composite material for pantograph slide plate |
| CN104711774A (en) * | 2015-03-31 | 2015-06-17 | 赵晓明 | Full-carbon-fiber weftless cloth containing carbon-fiber filaments in positive and negative 45-degree directions and preparation method thereof |
| CN104999724A (en) * | 2015-07-02 | 2015-10-28 | 河北立格环保科技有限公司 | Carbon fiber oxygen-rich filament needled felt and preparation method and application thereof |
| CN105038116A (en) * | 2015-08-26 | 2015-11-11 | 江南大学 | Deep-crosslinked-structure carbon-fiber-reinforced phenolic-resin-base friction material and preparation method thereof |
| CN105332166A (en) * | 2015-11-23 | 2016-02-17 | 江南大学 | Two-layer variable density carbon fiber needling preform and preparation method thereof |
| CN105801146A (en) * | 2016-04-15 | 2016-07-27 | 航天材料及工艺研究所 | Continuous density gradient low-density porous carbon bonding composite material and preparing method thereof |
| CN106431444A (en) * | 2015-02-27 | 2017-02-22 | 通用电气公司 | Ceramic matrix composite structures with controlled microstructures fabricated using chemical vapor infiltration (cvi) |
| EP3208484A1 (en) * | 2015-12-28 | 2017-08-23 | Goodrich Corporation | Needled brake disks and methods |
| CN107287882A (en) * | 2017-05-05 | 2017-10-24 | 航天材料及工艺研究所 | Lightening fire resistant thermally protective materials and preparation method thereof |
| CN109228546A (en) * | 2018-08-22 | 2019-01-18 | 青岛高泰新材料有限公司 | A kind of preparation method of high density multi-angle establishment carbon fiber carbon carbon cylinder |
| US10457016B2 (en) | 2016-02-23 | 2019-10-29 | Honeywell International Inc. | Differential needling of a carbon fiber preform |
| CN110735998A (en) * | 2019-09-11 | 2020-01-31 | 蓝箭航天空间科技股份有限公司 | carrier rocket power pipeline system heat insulation structure and carrier rocket |
| CN113308796A (en) * | 2021-04-25 | 2021-08-27 | 上海大学绍兴研究院 | Structure-reinforced needling preform for carbon/carbon composite material, carbon/carbon composite material and preparation method of carbon/carbon composite material |
| CN113502606A (en) * | 2021-06-30 | 2021-10-15 | 浙江星辉新材料科技有限公司 | Carbon brake disc preform and preparation method thereof |
| CN115611645A (en) * | 2022-10-28 | 2023-01-17 | 航天材料及工艺研究所 | Carbon-ceramic hybrid matrix gradient structure composite material and preparation method thereof |
| WO2023124122A1 (en) * | 2021-12-30 | 2023-07-06 | 隆基绿能科技股份有限公司 | Carbon fiber preform and production method therefor, and high-temperature-resistant carbon-carbon composite |
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| CN101503844A (en) * | 2009-03-02 | 2009-08-12 | 宜兴市飞舟高新科技材料有限公司 | Pre-oxidized fiber filament / pre-oxidized fiber net tire composite pricking prefabricated body and method for manufacturing the same |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691338A (en) * | 2014-12-20 | 2015-06-10 | 中南大学 | Producing method of copper wire mesh modified carbon/carbon composite material for pantograph slide plate |
| CN106431444A (en) * | 2015-02-27 | 2017-02-22 | 通用电气公司 | Ceramic matrix composite structures with controlled microstructures fabricated using chemical vapor infiltration (cvi) |
| CN115626833A (en) * | 2015-02-27 | 2023-01-20 | 通用电气公司 | Ceramic matrix composite structures with controlled microstructure prepared with Chemical Vapor Infiltration (CVI) |
| CN104711774A (en) * | 2015-03-31 | 2015-06-17 | 赵晓明 | Full-carbon-fiber weftless cloth containing carbon-fiber filaments in positive and negative 45-degree directions and preparation method thereof |
| CN104999724A (en) * | 2015-07-02 | 2015-10-28 | 河北立格环保科技有限公司 | Carbon fiber oxygen-rich filament needled felt and preparation method and application thereof |
| CN105038116A (en) * | 2015-08-26 | 2015-11-11 | 江南大学 | Deep-crosslinked-structure carbon-fiber-reinforced phenolic-resin-base friction material and preparation method thereof |
| CN105332166A (en) * | 2015-11-23 | 2016-02-17 | 江南大学 | Two-layer variable density carbon fiber needling preform and preparation method thereof |
| EP3208484A1 (en) * | 2015-12-28 | 2017-08-23 | Goodrich Corporation | Needled brake disks and methods |
| US10371222B2 (en) | 2015-12-28 | 2019-08-06 | Goodrich Corporation | Needled brake disks and methods |
| US10533620B2 (en) | 2015-12-28 | 2020-01-14 | Goodrich Corporation | Needled brake disks and methods |
| US10457016B2 (en) | 2016-02-23 | 2019-10-29 | Honeywell International Inc. | Differential needling of a carbon fiber preform |
| CN105801146A (en) * | 2016-04-15 | 2016-07-27 | 航天材料及工艺研究所 | Continuous density gradient low-density porous carbon bonding composite material and preparing method thereof |
| CN105801146B (en) * | 2016-04-15 | 2018-12-21 | 航天材料及工艺研究所 | Low density porous carbon bonding composites of gradient of continuous densityization and preparation method thereof |
| CN107287882A (en) * | 2017-05-05 | 2017-10-24 | 航天材料及工艺研究所 | Lightening fire resistant thermally protective materials and preparation method thereof |
| CN109228546A (en) * | 2018-08-22 | 2019-01-18 | 青岛高泰新材料有限公司 | A kind of preparation method of high density multi-angle establishment carbon fiber carbon carbon cylinder |
| CN109228546B (en) * | 2018-08-22 | 2020-07-10 | 青岛高泰新材料有限公司 | Preparation method of high-density multi-angle woven carbon fiber carbon cylinder |
| CN110735998B (en) * | 2019-09-11 | 2020-10-16 | 蓝箭航天空间科技股份有限公司 | Carrier rocket power pipeline system heat insulation structure and carrier rocket |
| CN110735998A (en) * | 2019-09-11 | 2020-01-31 | 蓝箭航天空间科技股份有限公司 | carrier rocket power pipeline system heat insulation structure and carrier rocket |
| CN113308796A (en) * | 2021-04-25 | 2021-08-27 | 上海大学绍兴研究院 | Structure-reinforced needling preform for carbon/carbon composite material, carbon/carbon composite material and preparation method of carbon/carbon composite material |
| CN113502606A (en) * | 2021-06-30 | 2021-10-15 | 浙江星辉新材料科技有限公司 | Carbon brake disc preform and preparation method thereof |
| WO2023124122A1 (en) * | 2021-12-30 | 2023-07-06 | 隆基绿能科技股份有限公司 | Carbon fiber preform and production method therefor, and high-temperature-resistant carbon-carbon composite |
| CN115611645A (en) * | 2022-10-28 | 2023-01-17 | 航天材料及工艺研究所 | Carbon-ceramic hybrid matrix gradient structure composite material and preparation method thereof |
| CN115611645B (en) * | 2022-10-28 | 2023-05-12 | 航天材料及工艺研究所 | Carbon-ceramic hybrid matrix gradient structure composite material and preparation method thereof |
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