CN103921453A - Mold closing hydraulic assisted prepreg molding process method - Google Patents
Mold closing hydraulic assisted prepreg molding process method Download PDFInfo
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- CN103921453A CN103921453A CN201310646991.6A CN201310646991A CN103921453A CN 103921453 A CN103921453 A CN 103921453A CN 201310646991 A CN201310646991 A CN 201310646991A CN 103921453 A CN103921453 A CN 103921453A
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- prepreg
- fabric
- resin
- dry state
- rtm
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Classifications
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- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- 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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Robotics (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to the technical field of low cost manufacturing of high performance composite materials, and relates to a mold closing hydraulic assisted prepreg molding process method similar to a RTM (resin transfer molding) molding process. The mold closing hydraulic assisted prepreg molding process method is a low cost molding process method using liquid resin, introduced into a closed mold cavity, as a pressure transmitting medium to provide a curing pressure required by curing of a prepreg composite to prepare a high performance composite material. According to the structure characteristics of a composite part, a prepreg and a dry fiber fabric are taken in a certain proportion and combination mode, and then are paved and prefabricated, and the mold closing compression amount can be realized by the dry fiber fabric with compression deformation property. A preformed body is paved in an opposite mold closing cavity for RTM molding, a mold is closed, and RTM resin which is same with prepreg resin and can be completely compatible is injected, so that the dry fiber fabric is wetted, and solidification compaction of the prepreg can be realized with the help of a liquid pressure field formed by the RTM resin in the closed mold.
Description
Technical field
The invention belongs to the research of high-performance composite materials low-cost manufacturing technique, relate to a kind of prepreg mold closing hydraulic pressure auxiliary molding technique of the RTM of being similar to moulding process.
Background technology
Composite has excellent specific strength, specific stiffness because of it, excellent fatigue behaviour and durability, and structure designability has been proved and can significantly alleviates construction weight; Therefore be widely used with external advanced person's fighter plane on.And opportunity of combat is more advanced, the consumption of composite is higher, and this trend has represented the developing direction of advanced opportunity of combat to composite demand.
At present both at home and abroad composite material process planning is topmost is autoclave forming process, is suitable for the relatively low covering of large scale, complex structure degree, the manufacture of wallboard class composite product.Prepreg composite can ensure higher fiber volume fraction and fiber collimation, therefore has excellent in-plane mechanical properties.But there is the composite product of labyrinth for beam, frame, rib and overall box section etc., adopt more difficult realization of autoclave forming process.
Liquid condition shaping technique especially resin transfer moulding (RTM) technique, as a kind of novel composite material process planning technology, is the main flow of aviation composite low-cost manufacturing technique development in recent years.RTM technique is a kind of closed moulding technique, and its technological principle is in airtight die cavity, by pressure-driven resin flows and complete the infiltration to dry state perform manufacturing.Compared with traditional prepreg-autoclave forming process, although that RTM technique has manufacturing dimension precision is high, the advantage that product yield rate is high, is particularly useful for having the integration manufacture of labyrinth composite product, can significantly reduce assembly cost.But composite volume integral number prepared by RTM technique is low compared with the volume fraction of prepreg composite, causes its mechanical property decrease to some degree.
Summary of the invention
The object of the invention is: propose a kind of simultaneously not obvious reduction composite materials property again of composite product that can moulding labyrinth, be similar to the prepreg mold closing hydraulic pressure auxiliary molding technique of RTM moulding process.
Technical scheme of the present invention is: a kind of prepreg mold closing hydraulic pressure auxiliary molding technique, it is characterized in that, and preform structure is divided into the preimpregnation bed of material and dry state fiber fabric layer; Prepreg and dry state fabric combination paving are obtained to perform manufacturing, and wherein prepreg overlay quantity is 50%～80% of preform laying sum, and dry state fabric laying quantity is 20%～50% of preform laying sum; Preform is placed on to RTM moulding with in the die cavity of close die, matched moulds is to nominal thickness, inject RTM moulding resin, complete solidifying of prepreg/dry state fabric coforming composite according to the curing process of selected resin system, the demoulding obtains composite.
In described preform the preimpregnation bed of material and dry state fiber fabric layer be alternate combinations or one side for prepreg laminated for dry state fiber fabric layer or upper and lower surface be in the middle of dry state fiber fabric layer to be the preimpregnation bed of material.
The selected fibre reinforcement of described prepreg is the shuffling body of a kind of or above-mentioned fiber in glass fibre, carbon fiber, aramid fiber, basalt fibre, and its weaving form is one-way fabric or plain cloth or satin fabric or twills or nonwoven or without latitude cloth or non-flexing fabric.
The selected fibre reinforcement of described dry state fabric is the shuffling body of a kind of or above-mentioned fiber in glass fibre, carbon fiber, aramid fiber, basalt fibre, and its weaving form is one-way fabric or plain cloth or satin fabric or twills or nonwoven or without latitude cloth or non-flexing fabric.
Kinds of fibers and the weaving form of the described dry state fabric enhancing fabric used with prepreg are identical.
The prepolymer of the selected resin matrix of described prepreg or RTM moulding resin identical with RTM moulding resin, resin matrix is epoxy resin or cyanate ester resin or bimaleimide resin or thermoset polyimide resin or unsaturated polyester resin.
It is compound that described prepreg and dry state fabric are realized co-curing in RTM molding process, and the technological parameter of its injection technique, curing process and selected matrix resin is as good as.
Advantage of the present invention is: prepreg autoclave forming process is combined with RTM moulding process, both the in-plane mechanical properties of prepreg composite excellence and good paving coating process can be brought into play, and the flexibility of labyrinth composite product can be manufactured in conjunction with RTM technology again.By the ratio of prepreg and dry state fabric in the design preform becoming more meticulous, utilize paving to provide RTM moulding process needed matched moulds decrement at the dry state fabric of prepreg overlay upper and lower surface, overcome the technological problems that prepreg overlay is difficult to compression, in mold closing RTM injection molding technique, injecting resin becomes the medium of transmission of pressure simultaneously, form even, controlled pressure field by the flow passage system of appropriate design, provide prepreg to solidify required solidifying pressure, ensure the compaction of prepreg.In covering, wall panel structure, adopt prepreg, to keep higher in-plane mechanical properties and excellent anufacturability, and adopt RTM technique in the structures such as beam, rib, reinforcement, farthest bring into play its structure manufacturability flexibly.Adopt this novel forming technology that combines prepreg and RTM advantage, can obtain the high fiber volume fraction that dimensional accuracy is high, surface quality is good, the high-performance of high in-plane mechanical properties, low cost composites structural member, remove the cementing operation of panel and reinforcement from, avoided again RTM technique to manufacture the technological difficulties of large scale, large thickness simple surface structure product simultaneously.
Detailed description of the invention
By preform structural design, preform structure is divided into the preimpregnation bed of material and dry state fiber fabric layer, prepreg and dry state fabric, according to certain ratio and combination paving, are obtained to perform manufacturing.Preform is placed on to RTM moulding with in the die cavity of close die, realizes the matched moulds decrement of preform by dry state fabric.Matched moulds also injects RTM moulding resin, in completing the infiltration of dry state fabric, as pressure transmission medium, provides prepreg composite material solidification required solidifying pressure.Finally obtain having concurrently the excellent precasting process of prepreg composite, higher in-plane mechanical properties and the high-performance and low-cost composite of the flexible manufacturability of RTM forming composite, its processing step is as follows:
A) prepreg and the paving of dry state fabric are obtained to perform manufacturing, wherein prepreg overlay quantity is 50%～80% of preform laying sum, and dry state fabric laying quantity is 20%～50% of preform laying sum;
B) preform is placed on to RTM moulding with in the die cavity of close die, utilize dry state fiber fabric layer to realize the matched moulds compressibility of preform, matched moulds is to nominal thickness, its volume fraction is between 50%～63%, inject RTM moulding resin, in completing the infiltration of dry state fiber fabric layer, as pressure transmission medium, provide prepreg composite material solidification required solidifying pressure;
C) complete solidifying of prepreg/dry state fabric coforming composite according to the curing process of selected resin system, the demoulding obtains composite.
Below in conjunction with specific embodiment, the present invention is described in further details.
Specific embodiment 1
Select typical aviation high temperature RTM epoxy resin as matrix resin, its pre-polymerization 30min at 160 DEG C is obtained to prepreg grade resins matrix.Select domestic U3160 carbon fiber one-way laid fabric as reinforcement, utilize hot melt to prepare U3160/ epoxy prepreg, the domestic U3160 carbon fiber one-way laid fabric of the same selection of dry state fabric.First paving prepreg preform, laying number is 9 layers, at upper and lower surface 2 layers of unidirectional laid fabric of U3160 of paving respectively of prepreg preform, obtain prepreg/dry state fabric preform, place it in RTM moulding close die, matched moulds is compressed to 2mm thickness, injects after RTM epoxy resin to preform infiltrates completely and heats up and solidify.Wherein, injection technological parameter is identical with the technological parameter of selected RTM resin with curing process parameter.After solidifying end, be cooled to room temperature, the demoulding.Prepreg/dry state carbon fiber preform is realized co-curing under RTM moulding process, and interface is in conjunction with good, and the composite fiber volume fraction finally obtaining is about 59%.
Specific embodiment 2
Select typical aviation RTM bimaleimide resin as matrix resin, its pre-polymerization 90min at 130 DEG C is obtained to prepreg grade resins matrix.Select domestic CF3031 carbon fiber twills as reinforcement, utilize hot melt to prepare CF3031/ bismaleimide resin prepreg, the domestic CF3031 carbon fiber twills of the same selection of dry state fabric.First paving prepreg preform, laying number is 10 layers, at upper and lower surface 2 layers of CF3031 carbon fiber twills of paving respectively of prepreg preform, obtain prepreg/dry state fabric preform, place it in RTM moulding close die, matched moulds is compressed to 3mm thickness, injects after RTM bimaleimide resin to preform infiltrates completely and heats up and solidify.Wherein, injection technological parameter is identical with the technological parameter of selected RTM resin with curing process parameter.After solidifying end, be cooled to room temperature, the demoulding.Prepreg/dry state carbon fiber preform is realized co-curing under RTM moulding process, and interface is in conjunction with good, and the composite fiber volume fraction finally obtaining is about 58%.
Specific embodiment 3
Select warm RTM epoxy resin in typical aviation use as matrix resin, its pre-polymerization 30min at 90 DEG C to be obtained to prepreg grade resins matrix.Select SW280 glass fibre satin fabric as reinforcement, utilize hot melt to prepare SW280/ epoxy prepreg, dry state fabric is selected SW280 glass fibre satin fabric equally.First paving prepreg preform, laying number is 10 layers, at upper and lower surface 2 layers of SW280 glass fibre satin fabric of paving respectively of prepreg preform, obtain prepreg/dry state fabric preform, place it in RTM moulding close die, matched moulds is compressed to 3mm thickness, and injection temperature RTM epoxy resin to preform heats up and solidifies after infiltrating completely.Wherein, injection technological parameter is identical with the technological parameter of selected RTM resin with curing process parameter.After solidifying end, be cooled to room temperature, the demoulding.Prepreg/dry state carbon fiber preform is realized co-curing under RTM moulding process, and interface is in conjunction with good, and the composite fiber volume fraction finally obtaining is about 51%.
Specific embodiment 4
Select warm RTM epoxy resin in typical aviation use as matrix resin, its pre-polymerization 30min at 90 DEG C to be obtained to prepreg grade resins matrix.Select domestic U3160 carbon fiber one-way laid fabric as reinforcement, utilize hot melt to prepare U3160/ epoxy prepreg, the domestic U3160 carbon fiber one-way laid fabric of the same selection of dry state fabric.First, utilize dry state fabric paving to cover two C type beams, the laying number of dry state fabric is 10 layers, then two C type beams are combined as to the web structure in I-beam.Cover 22 layers of prepreg of the each paving in upper and lower surface of the web structure forming dry state fabric paving, obtain the I-beam preform that prepreg/dry state fabric combines, place it in RTM moulding close die, matched moulds, wherein the thickness after the compression of prepreg/dry state fabric combination preform is 5mm.Inject after RTM epoxy resin to preform infiltrates completely and heat up and solidify.Wherein, injection technological parameter is identical with the technological parameter of selected RTM resin with curing process parameter.After solidifying end, be cooled to room temperature, the demoulding.Prepreg/dry state carbon fiber preform is realized co-curing under RTM moulding process, and interface is in conjunction with good, and the composite fiber volume fraction finally obtaining is about 58%.
Specific embodiment 5
Select typical aviation RTM bimaleimide resin as matrix resin, its pre-polymerization 90min at 130 DEG C is obtained to prepreg grade resins matrix.Select U7192 carbon fiber one-way laid fabric as reinforcement, utilize hot melt to prepare U7192/ bismaleimide resin prepreg, dry state fabric is selected U7192 carbon fiber one-way laid fabric equally.First, utilize dry state fabric paving to cover four shape of the mouth as one speaks beams, two C type beam preforms, more above-mentioned dry state fabric preform is combined to form to the combined type preform of Multiple cavity box segment structure form, the laying number of dry state fabric is 15 layers.At 37 layers of prepreg of the each paving in upper and lower surface of dry state fabric combination preform, obtain the Multiple cavity box segment structure preform that prepreg/dry state fabric combines, place it in RTM moulding close die, matched moulds, wherein the thickness after the compression of prepreg/dry state fabric combination preform is 10mm.Inject after RTM bimaleimide resin to preform infiltrates completely and heat up and solidify.Wherein, injection technological parameter is identical with the technological parameter of selected RTM resin with curing process parameter.After solidifying end, be cooled to room temperature, the demoulding.Prepreg/dry state carbon fiber preform is realized co-curing under RTM moulding process, and interface is in conjunction with good, and the composite fiber volume fraction finally obtaining is about 56%.
Specific embodiment 6
Select typical RTM High temp. epoxy resins as matrix resin, its pre-polymerization 30min at 160 DEG C is obtained to prepreg grade resins matrix.Select domestic CF3031 carbon fiber twills as reinforcement, utilize hot melt to prepare CF3031/ epoxy prepreg, dry state fabric is selected CF3031 carbon fiber twills equally.First utilize prepreg to complete the paving of T-shaped reinforcement preform in labyrinth composite orthogonal stiffeners rib, prepreg overlay number is 12 layers, reinforcement preform is combined in RTM mould, at its surperficial paving dry state fabric, the laying number of dry state fabric is 12 layers, matched moulds, wherein the thickness after the compression of prepreg/dry state fabric combination preform is 6mm.Inject after RTM High temp. epoxy resins to preform infiltrates completely and heat up and solidify.Wherein, injection technological parameter is identical with the technological parameter of selected RTM resin with curing process parameter.After solidifying end, be cooled to room temperature, the demoulding.Prepreg/dry state carbon fiber preform is realized co-curing under RTM moulding process, and interface is in conjunction with good, and the composite fiber volume fraction finally obtaining is about 60%.
Claims (7)
1. a prepreg mold closing hydraulic pressure auxiliary molding technique, is characterized in that, preform structure is divided into the preimpregnation bed of material and dry state fiber fabric layer; Prepreg and dry state fabric combination paving are obtained to perform manufacturing, and wherein prepreg overlay quantity is 50%～80% of preform laying sum, and dry state fabric laying quantity is 20%～50% of preform laying sum; Preform is placed on to RTM moulding with in the die cavity of close die, matched moulds is to nominal thickness, inject RTM moulding resin, complete solidifying of prepreg/dry state fabric coforming composite according to the curing process of selected resin system, the demoulding obtains composite.
2. a kind of prepreg mold closing hydraulic pressure auxiliary molding technique as claimed in claim 1, it is characterized in that, in described preform the preimpregnation bed of material and dry state fiber fabric layer be alternate combinations or one side for prepreg laminated for dry state fiber fabric layer or upper and lower surface be in the middle of dry state fiber fabric layer to be the preimpregnation bed of material.
3. a kind of prepreg mold closing hydraulic pressure auxiliary molding technique as claimed in claim 1, it is characterized in that, the prepolymer of the selected resin matrix of described prepreg or RTM moulding resin identical with RTM moulding resin, resin matrix is epoxy resin or cyanate ester resin or bimaleimide resin or thermoset polyimide resin or unsaturated polyester resin.
4. a kind of prepreg mold closing hydraulic pressure auxiliary molding technique as claimed in claim 1, it is characterized in that, the selected fibre reinforcement of described prepreg is the shuffling body of a kind of or above-mentioned fiber in glass fibre, carbon fiber, aramid fiber, basalt fibre, and its weaving form is one-way fabric or plain cloth or satin fabric or twills or nonwoven or without latitude cloth or non-flexing fabric.
5. a kind of prepreg mold closing hydraulic pressure auxiliary molding technique as claimed in claim 1, it is characterized in that, the selected fibre reinforcement of described dry state fabric is the shuffling body of a kind of or above-mentioned fiber in glass fibre, carbon fiber, aramid fiber, basalt fibre, and its weaving form is one-way fabric or plain cloth or satin fabric or twills or nonwoven or without latitude cloth or non-flexing fabric.
6. a kind of prepreg mold closing hydraulic pressure auxiliary molding technique as claimed in claim 1, is characterized in that, kinds of fibers and the weaving form of the described dry state fabric enhancing fabric used with prepreg are identical.
7. a kind of prepreg mold closing hydraulic pressure auxiliary molding technique as claimed in claim 1, it is characterized in that, it is compound that described prepreg and dry state fabric are realized co-curing in RTM molding process, and the technological parameter of its injection technique, curing process and selected matrix resin is as good as.
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| CN201310646991.6A CN103921453A (en) | 2013-12-04 | 2013-12-04 | Mold closing hydraulic assisted prepreg molding process method |
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| CN201310646991.6A CN103921453A (en) | 2013-12-04 | 2013-12-04 | Mold closing hydraulic assisted prepreg molding process method |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104945854A (en) * | 2015-07-23 | 2015-09-30 | 北京化工大学 | Preparation method for short carbon fiber interlayer-reinforced fiber composite material |
| CN106976281A (en) * | 2017-03-21 | 2017-07-25 | 安徽四创电子股份有限公司 | The radar antenna of carbon fibre composite and preparation method and application material |
| CN107032658A (en) * | 2017-06-07 | 2017-08-11 | 国电联合动力技术有限公司 | A kind of carbon fibre composite and preparation method thereof |
| CN107215039A (en) * | 2017-06-07 | 2017-09-29 | 国电联合动力技术有限公司 | A kind of core filled composite material and preparation method thereof |
| CN108015923A (en) * | 2017-11-23 | 2018-05-11 | 宁波伯骏智能科技有限公司 | A kind of processing and forming technology of fiber reinforced thermolplastic composite material product |
| CN108183181A (en) * | 2017-12-27 | 2018-06-19 | 天津中科先进技术研究院有限公司 | Manufacturing method of electric vehicle battery pack and battery pack |
| CN108943765A (en) * | 2018-09-21 | 2018-12-07 | 吉林省华阳新材料研发有限公司 | A kind of production method of Basalt fiber products |
| CN109334045A (en) * | 2018-11-16 | 2019-02-15 | 航天特种材料及工艺技术研究所 | A kind of cavity body structure and preparation method thereof |
| EP3711934A1 (en) * | 2019-03-19 | 2020-09-23 | ROXEL France | Composite material and method for manufacturing such a composite material |
| CN113276445A (en) * | 2021-06-17 | 2021-08-20 | 航天特种材料及工艺技术研究所 | Forming method of composite material capable of being pressed in all directions |
| CN114633495A (en) * | 2022-03-18 | 2022-06-17 | 安徽玄离智能科技股份有限公司 | Carbon fiber material paving and curing process for underground inspection robot |
| CN115716275A (en) * | 2021-08-26 | 2023-02-28 | 航天特种材料及工艺技术研究所 | C-shaped multi-rib cavity tubular mechanical arm made of carbon fiber composite material and manufacturing method |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104945854A (en) * | 2015-07-23 | 2015-09-30 | 北京化工大学 | Preparation method for short carbon fiber interlayer-reinforced fiber composite material |
| CN106976281A (en) * | 2017-03-21 | 2017-07-25 | 安徽四创电子股份有限公司 | The radar antenna of carbon fibre composite and preparation method and application material |
| CN107032658B (en) * | 2017-06-07 | 2023-02-28 | 国电联合动力技术有限公司 | Carbon fiber composite material and preparation method thereof |
| CN107032658A (en) * | 2017-06-07 | 2017-08-11 | 国电联合动力技术有限公司 | A kind of carbon fibre composite and preparation method thereof |
| CN107215039A (en) * | 2017-06-07 | 2017-09-29 | 国电联合动力技术有限公司 | A kind of core filled composite material and preparation method thereof |
| CN107215039B (en) * | 2017-06-07 | 2023-03-14 | 国电联合动力技术有限公司 | Sandwich composite material and preparation method thereof |
| CN108015923A (en) * | 2017-11-23 | 2018-05-11 | 宁波伯骏智能科技有限公司 | A kind of processing and forming technology of fiber reinforced thermolplastic composite material product |
| CN108183181A (en) * | 2017-12-27 | 2018-06-19 | 天津中科先进技术研究院有限公司 | Manufacturing method of electric vehicle battery pack and battery pack |
| CN108943765A (en) * | 2018-09-21 | 2018-12-07 | 吉林省华阳新材料研发有限公司 | A kind of production method of Basalt fiber products |
| CN109334045A (en) * | 2018-11-16 | 2019-02-15 | 航天特种材料及工艺技术研究所 | A kind of cavity body structure and preparation method thereof |
| CN109334045B (en) * | 2018-11-16 | 2020-11-13 | 航天特种材料及工艺技术研究所 | Cavity structure and preparation method thereof |
| EP3711934A1 (en) * | 2019-03-19 | 2020-09-23 | ROXEL France | Composite material and method for manufacturing such a composite material |
| FR3093948A1 (en) * | 2019-03-19 | 2020-09-25 | Roxel France | Composite material and method of making such a composite material |
| CN113276445B (en) * | 2021-06-17 | 2022-07-08 | 航天特种材料及工艺技术研究所 | Forming method of composite material capable of being pressed in all directions |
| CN113276445A (en) * | 2021-06-17 | 2021-08-20 | 航天特种材料及工艺技术研究所 | Forming method of composite material capable of being pressed in all directions |
| CN115716275A (en) * | 2021-08-26 | 2023-02-28 | 航天特种材料及工艺技术研究所 | C-shaped multi-rib cavity tubular mechanical arm made of carbon fiber composite material and manufacturing method |
| CN115716275B (en) * | 2021-08-26 | 2024-07-02 | 航天特种材料及工艺技术研究所 | C-shaped multi-rib cavity tubular mechanical arm made of carbon fiber composite material and manufacturing method |
| CN114633495A (en) * | 2022-03-18 | 2022-06-17 | 安徽玄离智能科技股份有限公司 | Carbon fiber material paving and curing process for underground inspection robot |
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Application publication date: 20140716 |