CN105479780A - Preparation method of fiber-resin composite material and purpose of method - Google Patents
Preparation method of fiber-resin composite material and purpose of method Download PDFInfo
- Publication number
- CN105479780A CN105479780A CN201510827353.3A CN201510827353A CN105479780A CN 105479780 A CN105479780 A CN 105479780A CN 201510827353 A CN201510827353 A CN 201510827353A CN 105479780 A CN105479780 A CN 105479780A
- Authority
- CN
- China
- Prior art keywords
- preparation
- resin composite
- temperature
- fibre
- fiber
- Prior art date
- 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.)
- Pending
Links
Classifications
-
- 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
- B29C71/00—After-treatment of articles without altering their shape; Apparatus therefor
- B29C71/02—Thermal after-treatment
-
- 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
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
-
- 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
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/16—Cooling
-
- 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
- B29C71/00—After-treatment of articles without altering their shape; Apparatus therefor
- B29C71/02—Thermal after-treatment
- B29C2071/022—Annealing
Landscapes
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Oral & Maxillofacial Surgery (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
The invention discloses a preparation method of a fiber-resin composite material and the purpose of the method. The preparation method comprises the following steps of treating a solidified-shaped material under a certain temperature; and/or under a vacuum condition, and after the material is treated at 50-300 DEG C, testing the weight and the composition of the fiber-resin composite material. The preparation method of the fiber-resin composite material disclosed by the invention is used for manufacturing members based on the fiber-resin composite material. Compared with the prior art, the preparation method disclosed by the invention has the following beneficial effects that high-and-low temperature alternating treatment is performed on the solidified-shaped fiber-reinforced resinous substrate composite material, so that residual stress of the solidified-shaped fiber reinforcing resinous substrate composite material during high temperature solidification is released, the property of the material/member achieves a stable state, and during the using process of the material/member, the changes of dimensions and properties caused by creeping and stress relaxation are reduced.
Description
Technical field
The invention belongs to composite processing field, be a kind of method for polymer matrix composites size and stable performance process, be specially a kind of preparation method of fibre-resin composite and the purposes of the method.
Background technology
Polymer matrix composites strengthen polymer matrix composites by continuous fiber/chopped strand and form, and because resin matrix is macromolecular material, have remaining Small molecular and moisture after curing molding in material; In use, due to the release of Small molecular and moisture, dimensional accuracy, the performance of structure can change.In addition, due to composite curing molding under uniform temperature condition, after solidification, temperature return has residual stress at material/component inside, and macromolecular material in use stress discharges gradually, and the dimensional accuracy of structure also can change.
In order in use guarantee that the dimensional accuracy of material/component is stablized and stable performance, de-stress being carried out to the component after shaping, removes remaining micromolecular PROCESS FOR TREATMENT.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of preparation method of fibre-resin composite and the purposes of the method.
The present invention is achieved by the following technical solutions:
First aspect, the invention provides a kind of preparation method of fibre-resin composite, it comprises the steps:
Material shaping for immobilization is carried out high-temperature stable process at 20 ~ 500 DEG C; And/or
Under vacuum, after processing in 50 ~ 300 DEG C, the weight of test fibre-resin composite and composition.
Preferably, the concrete operations of described high-temperature stable process are:
Carried out successively by material shaping for immobilization heating up and lowering the temperature, be a circulation once to heat up and once to lower the temperature, the number of times controlling described circulation is at least twice.
Preferably, the temperature after described intensification is 200 ~ 400 DEG C, and the temperature after cooling is-220 ~-150 DEG C, and the speed of intensification and cooling is 0.1 ~ 10 DEG C/min.
Preferably, temperature retention time during described operation at 200 ~ 400 DEG C and-220 ~-150 DEG C is 0 ~ 200h, and the number of times of described circulation is 1 ~ 200 time.
Preferably, described 50 ~ 300 DEG C is obtain with the ramp of 0.1 ~ 10 DEG C/min.
Preferably, the vacuum of described vacuum condition is 10
-3pa.
Preferably, the time of described process is 1 ~ 200h.
Second aspect, present invention also offers a kind of purposes of preparation method in the manufacture of the component based on fibre-resin composite of fibre-resin composite as the aforementioned.
The present invention by increasing high/low temperature/vacuum high-temperature process after composite material forming, make it more than gel point, carry out Stress Release/Small molecular, residual moisture is discharged, solve the shaping rear precision of fiber-reinforced resin matrix compound material unstable, it is in high accuracy, the structural application restricted problem of high stable.Achieve the high accuracy of polymer matrix composites, high stable manufacture, can be used for the production by lightening technology for making of the precision components such as Satellite Payloads supporting member, payload and astronomical observation telescope.
Described composite comprises carbon fiber, glass fibre, quartz fibre and various organic and inorganic fiber and thermosetting resin, comprise the various combinations of epoxy resin, cyanate ester resin, but be not limited only to above listed fiber and resin, by various moulding process, comprise shaping material or the components such as autoclave, baking oven, mold pressing, RTM, winding.
Compared with prior art, the present invention has following beneficial effect:
1, by carrying out the process of high/low temperature alternation to the fiber-reinforced resin matrix compound material of curing molding, make its when hot setting residual stress release, make the state that the performance of material/component reaches stable, reduce the change of size and the performance in use caused due to creep and stress relaxation;
2, remaining in Small molecular and the moisture of material/component inside by discharging under high temperature and high vacuum condition, making size and the stable performance of material, when space environment uses, due to high vacuum size therefore and performance change reduction;
3, by the collection of volatile matter can be coagulated, can analyze and remain in micromolecular composition in material/component, be convenient to subsequent material and improve and optimize.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the high/low temperature loop stabilization processing technological flow figure in the present invention;
Fig. 2 is the vacuum high-temperature stabilizing treatment technique flow chart in the present invention.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
embodiment 1
Present embodiment provides the method for composite/scantling, stable performance process; Preparation flow, as Fig. 1, specifically comprises the steps:
(1) clear up, weigh
Composite/component acetone (or alcohol) carries out removing surface, and weigh, keep a record.Material/the component cleared up is placed in container handling, closing containers, checks the sealing of container.
(2) high/low temperature loop stabilization processing procedure
A, material/component is placed in treatment facility;
B, to heat up with the heating rate of 1.5 ~ 2 DEG C/min, when being warming up to 130 DEG C, be incubated 3 hours, need in process to record temperature and time;
C, to lower the temperature with the rate of temperature fall of 1.5 ~ 2 DEG C/min, when being cooled to-50 DEG C, be incubated 3 hours, need in process to record temperature and time;
Each 3 times of D, above-mentioned B, C process that circulates.
(3) vacuum high-temperature stabilization processes
A, processing procedure are carried out in airtight container, and the material/sample after weighing is placed in treatment facility;
B, to heat up with the heating rate of 1.5 ~ 2 DEG C/min, when being warming up to 130 DEG C, be incubated 48 hours, need in process to record temperature and time;
C, open vacuum pump evacuation, until vacuum reaches 0.5 × 10 simultaneously
-3pa, keeps vacuum 48 hours;
D, keep temperature and vacuum process 48 hours;
E, Temperature fall, let out vacuum, when device interior temperature is lower than 30 DEG C, open tank body, take out material/component, weigh and record;
F, the quality receiving sampling and testing condensable material matter from collecting board and composition.
(4) quality of condensable material matter and component are analyzed.
Step (2) and step (3) can optionally one or its two.
The present embodiment achieves fiber-reinforced resin matrix compound material stabilization treatment method, excellent performance after process.
embodiment 2
Present embodiment provides the method for composite/scantling, stable performance process; Preparation flow, as Fig. 1, specifically comprises the steps:
(1) clear up, weigh
Composite/component acetone (or alcohol) carries out removing surface, and weigh, keep a record.Material/the component cleared up is placed in container handling, closing containers, checks the sealing of container.
(2) high/low temperature loop stabilization processing procedure
A, material/component is placed in treatment facility;
B, to heat up with the heating rate of 1.5 ~ 2 DEG C/min, when being warming up to 130 DEG C, be incubated 3 hours, need in process to record temperature and time;
C, to lower the temperature with the rate of temperature fall of 1.5 ~ 2 DEG C/min, when being cooled to-50 DEG C, be incubated 3 hours, need in process to record temperature and time;
Each 3 times of D, above-mentioned B, C process that circulates.
(3) vacuum high-temperature stabilization processes
A, processing procedure are carried out in airtight container, and the material/sample after weighing is placed in treatment facility;
B, to heat up with the heating rate of 1.5 ~ 2 DEG C/min, when being warming up to 130 DEG C, be incubated 48 hours, need in process to record temperature and time;
C, open vacuum pump evacuation, until vacuum reaches 0.5 × 10 simultaneously
-3pa, keeps vacuum 48 hours;
D, keep temperature and vacuum process 48 hours;
E, Temperature fall, let out vacuum, when device interior temperature is lower than 30 DEG C, open tank body, take out material/component, weigh and record;
F, the quality receiving sampling and testing condensable material matter from collecting board and composition.
(4) quality of condensable material matter and component are analyzed.
Step (2) and step (3) can optionally one or its two.
The present embodiment achieves fiber-reinforced resin matrix compound material stabilization treatment method, excellent performance after process
The invention has the advantages that:
1, by carrying out the process of high/low temperature alternation to the fiber-reinforced resin matrix compound material of curing molding, make its when hot setting residual stress release, make the state that the performance of material/component reaches stable, reduce the change of size and the performance in use caused due to creep and stress relaxation;
As: after certain composite material bracket assembling processing, flatness is 0.05mm, becomes 0.12mm after depositing a period of time; As processed the process of advance line stabilization after assembling, then place a period of time back plane degree at 0.06mm;
2, remaining in Small molecular and the moisture of material/component inside by discharging under high temperature and high vacuum condition, making size and the stable performance of material, when space environment uses, due to high vacuum size therefore and performance change reduction;
After processing according to the technique of embodiment (1), (3), (4), the vacuum deflation rate of carbon fiber/epoxy resin based composites is reduced to 0.3% from 0.64%, can coagulate volatile matter content and drop to 0.03% from 0.06%; Carbon fiber/cyanate composite material vacuum deflation rate is reduced to 0.2% from 0.32%, can coagulate volatile matter content and drop to 0.02% from 0.03%;
3, by the collection of volatile matter can be coagulated, can analyze and remain in micromolecular composition in material/component, be convenient to subsequent material and improve and optimize.
Such as: in residue, find dicyanamide component, can avoid when monomer synthesize or resin modified introducing the monomer containing dicyanamide component or modifier.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (8)
1. a preparation method for fibre-resin composite, is characterized in that, comprises the steps:
Material shaping for immobilization is carried out high-temperature stable process at 20 ~ 500 DEG C; And/or
Under vacuum, after processing in 50 ~ 300 DEG C, the weight of test fibre-resin composite and composition.
2. the preparation method of fibre-resin composite as claimed in claim 1, it is characterized in that, the concrete operations of described high-temperature stable process are:
Carried out successively by material shaping for immobilization heating up and lowering the temperature, be a circulation once to heat up and once to lower the temperature, the number of times controlling described circulation is at least twice.
3. the preparation method of fibre-resin composite as claimed in claim 2, it is characterized in that, the temperature after described intensification is 200 ~ 400 DEG C, and the temperature after cooling is-220 ~-150 DEG C, and the speed of intensification and cooling is 0.1 ~ 10 DEG C/min.
4. the preparation method of fibre-resin composite as claimed in claim 3, is characterized in that, temperature retention time during described operation at 200 ~ 400 DEG C and-220 ~-150 DEG C is 0 ~ 200h, and the number of times of described circulation is 1 ~ 200 time.
5. the preparation method of fibre-resin composite as claimed in claim 1, it is characterized in that, described 50 ~ 300 DEG C is obtain with the ramp of 0.1 ~ 10 DEG C/min.
6. the preparation method of the fibre-resin composite as described in claim 1 or 5, is characterized in that, the vacuum of described vacuum condition is 10
-3pa.
7. the preparation method of fibre-resin composite as claimed in claim 6, it is characterized in that, the time of described process is 1 ~ 200h.
8. the purposes of the preparation method of a fibre-resin composite as claimed in claim 1 in the manufacture of the component based on fibre-resin composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510827353.3A CN105479780A (en) | 2015-11-24 | 2015-11-24 | Preparation method of fiber-resin composite material and purpose of method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510827353.3A CN105479780A (en) | 2015-11-24 | 2015-11-24 | Preparation method of fiber-resin composite material and purpose of method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105479780A true CN105479780A (en) | 2016-04-13 |
Family
ID=55667211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510827353.3A Pending CN105479780A (en) | 2015-11-24 | 2015-11-24 | Preparation method of fiber-resin composite material and purpose of method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105479780A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107983168A (en) * | 2017-12-18 | 2018-05-04 | 安徽普朗膜技术有限公司 | The processing method of macromolecular filtering film |
| CN108724767A (en) * | 2017-04-25 | 2018-11-02 | 波音公司 | Thermoplastic composite component manufacturing system and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101723679A (en) * | 2009-12-14 | 2010-06-09 | 江苏澳盛复合材料科技有限公司 | Method for manufacturing carbon/carbon composite material |
| US20110163467A1 (en) * | 2009-08-26 | 2011-07-07 | Microsoft Corporation | Injection molding of parthaving nonuniform thickness |
| CN104228090A (en) * | 2014-09-15 | 2014-12-24 | 东华大学 | Method for modifying aramid fiber composite by subzero treatment |
-
2015
- 2015-11-24 CN CN201510827353.3A patent/CN105479780A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110163467A1 (en) * | 2009-08-26 | 2011-07-07 | Microsoft Corporation | Injection molding of parthaving nonuniform thickness |
| CN101723679A (en) * | 2009-12-14 | 2010-06-09 | 江苏澳盛复合材料科技有限公司 | Method for manufacturing carbon/carbon composite material |
| CN104228090A (en) * | 2014-09-15 | 2014-12-24 | 东华大学 | Method for modifying aramid fiber composite by subzero treatment |
Non-Patent Citations (1)
| Title |
|---|
| 刘娇文等: "冷热循环对M40碳纤维/氰酸酯复合材料影响的试验研究", 《航天器环境工程》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108724767A (en) * | 2017-04-25 | 2018-11-02 | 波音公司 | Thermoplastic composite component manufacturing system and method |
| CN108724767B (en) * | 2017-04-25 | 2022-03-18 | 波音公司 | Thermoplastic composite component manufacturing system and method |
| US11633931B2 (en) | 2017-04-25 | 2023-04-25 | The Boeing Company | Thermoplastic composite part manufacturing system and method |
| CN107983168A (en) * | 2017-12-18 | 2018-05-04 | 安徽普朗膜技术有限公司 | The processing method of macromolecular filtering film |
| CN107983168B (en) * | 2017-12-18 | 2020-10-20 | 安徽普朗膜技术有限公司 | Method for treating polymer filtration membrane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109607551B (en) | Silicon dioxide aerogel composite material and preparation method and application thereof | |
| KR101929285B1 (en) | Graphene oxide synthesized from pitch-based carbon fiber and manufacturing method thereof | |
| ATE535365T1 (en) | COMBINED VACUUM RESIN INFUSION PROCESS AND PREPREG AUTOCLAVE MOLDING PROCESS AND DEVICE FOR PRODUCING FIBER COMPOSITE COMPONENTS | |
| CN110627517B (en) | Gradient ultrahigh-temperature ceramic matrix composite material and preparation method thereof | |
| CN107226707B (en) | Preparation method of SiC/Si-B-C-Zr ceramic matrix composite material | |
| CN105479780A (en) | Preparation method of fiber-resin composite material and purpose of method | |
| CN113501723B (en) | Preparation method and device of fiber-reinforced ceramic matrix composite antenna housing/window | |
| Purslow et al. | Autoclave moulding of carbon fibre-reinforced epoxies | |
| CN103332943A (en) | Microstructure design and performance control method for preparing carbon-ceramic-based composite materials based on liquid silicon melt infiltration method | |
| CN108101566A (en) | The method that RTM technique auxiliary prepares carbon/silicon carbide ceramic matrix composite component | |
| US9669570B2 (en) | Process for injection moulding a composite part | |
| JP2944838B2 (en) | Method for manufacturing ceramic matrix composite material member | |
| CN110978562B (en) | Preparation method of high-temperature-resistant composite material cabin section | |
| CN110509578B (en) | Heat treatment method for improving shape memory performance of polyether-ether-ketone in 3D printing | |
| CN108995335A (en) | A kind of carbon fibre fabric reinforced polyether ether ketone base aviation composite and preparation method thereof | |
| CN110511008A (en) | High-compactness quartz/quartz composite material and preparation method based on freeze drying process | |
| Ou et al. | Study on the properties of resin transfer molding cyanate ester and its T800 grade carbon fiber composites | |
| CN110576621A (en) | Cyanate ester resin based near-zero expansion composite material truss rod and preparation method thereof | |
| US20090166936A1 (en) | Sol-Gel Process for the Manufacture of Moulds for Photocatalytic Processes | |
| Sun et al. | Effects of microwave drying on mechanical properties of wormwood stem | |
| CN110922616B (en) | Fiber reinforced polymer composite material and preparation method thereof | |
| CN110181637A (en) | A method of reducing timber band shrinkage | |
| US20210078266A1 (en) | Method for producing fiber-reinforced plastic from prepreg | |
| RU2007116914A (en) | METHOD FOR PRODUCING COMPOSITE MATERIAL WITH VOLUME NANOSTRUCTURE | |
| CN118163382A (en) | Preparation method of low-pore-space continuous fiber reinforced thermoplastic resin product |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160413 |
|
| RJ01 | Rejection of invention patent application after publication |