CN108016054A - Carbon fibre composite is molded membranous disc manufacturing process - Google Patents
Carbon fibre composite is molded membranous disc manufacturing process Download PDFInfo
- Publication number
- CN108016054A CN108016054A CN201711234088.3A CN201711234088A CN108016054A CN 108016054 A CN108016054 A CN 108016054A CN 201711234088 A CN201711234088 A CN 201711234088A CN 108016054 A CN108016054 A CN 108016054A
- Authority
- CN
- China
- Prior art keywords
- prepreg
- membranous disc
- carbon fibre
- fibre composite
- manufacturing process
- 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
- 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
- B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Carbon fibre composite is molded membranous disc manufacturing process.The invention discloses a kind of carbon fibre composite to be molded membranous disc manufacturing process, including the prepreg that prepreg is cut into definite shape and angle；Cleaning mold, coats releasing agent；The prepreg pre-add after cutting is heat-treated using heating platform；Laid to form the regular carbon fibre composite layer of shape；Using vacuum diaphragm bag encapsulation process, negative pressure is vacuumized；Curing is heated using baking oven；Carbon fibre composite layer is separated from mould after cooling；Cutting polishing is carried out to it, obtains the finished parts of carbon fibre composite shaping membranous disc.Membranous disc made from the method for the present invention has high-content fiber, surface-brightening bubble-free, and interfacial bonding strength reaches the effect of die press technology for forming, meets the requirement that aerospace navigational field produces carbon fiber composite material article.
Description
Technical field：
The present invention relates to a kind of carbon fibre composite to be molded membranous disc manufacturing process, more particularly to a kind of prepreg carbon fiber
Composite material, that is, mold closing internally pressuring shaping technique.
Background technology：
Resin-based carbon fiber strengthens phase composite materials, and quality is lighter than metallic aluminium, but intensity is higher than steel, and with resistance to
The characteristic of burn into high-modulus.With many excellent performances, the axial strength and modulus of carbon fiber are high, and density is low, higher than performance,
Without creep, superhigh temperature resistant under non-oxidizing atmosphere, fatigue durability is good, and between nonmetallic between metal, heat is swollen for specific heat and electric conductivity
Swollen coefficient is small and has anisotropy, good corrosion resistance, and radiolucency is good.Good electrical and thermal conductivity performance, electromagnetic wave shielding
OK etc..
Die press technology for forming be in composite material production a kind of most ancient and forming method rich in unlimited vigor it be
A certain amount of prepreg is added into metal in mould, heated, pressurization carrys out a kind of method of curing molding.The master of die press technology for forming
It is production efficiency height to want advantage, is easy to implement specialized and automated production, can effectively reduce manufacture cost；Product size precision
Height, it is reproducible；Any surface finish, without secondary modification；Can the baroque product of one-pass molding.The shortcoming of compression molding
It is mold manufacturing complexity, investment is larger.With metalworking technology, press manufacture level and synthetic resin processing performance not
It is disconnected to improve and develop, the forming temperature of molding compound and the relative reduction of pressure so that the productivity of compression molding product significantly carries
Height, quality progressively develop to the development that becomes more meticulous, size to maximization, can produce full-sized car component, bathtub, entirety at present and defend
Component etc. between life.
The content of the invention：
This is the purpose of the present invention is clearly a kind of carbon fibre composite shaping membranous disc manufacturing process, in order to solve existing skill
The problem of membranous disc that light weight, intensity are high, wearability is strong can not be produced in art with carbon fibre composite, and then provide a kind of
Carbon fibre composite is molded the manufacture craft of membranous disc.
Above-mentioned purpose is realized by following technical scheme：
A kind of carbon fibre composite is molded membranous disc manufacturing process, and the technique is realized by following steps：
Step 1, prepreg cutting processing procedure, including：The prepreg of web-like is assembled on rack, prepreg is being passed through
Paved on latitude cutting machine and calibrate spacing, debugging cutting machine, according to laying requirement and laying the difference of angle, according to cutting machine
The figure drawn is cut, and is repeated the above steps and is completed until all prepreg cloths are cut, and collects the preimpregnation cut
Material；
Step 2, membranous disc mold cleaning and prepreg warm：
First, membranous disc die surface is cleared up to free from admixture attachment state using acetone, it is then, equal in membranous disc die surface
The even epoxy resin release agent for coating 2-3 times, finally, the prepreg obtained using heating platform to step 1 cutting are preheated
Heating operation；
Step 3, prepreg laid course, including：
Step 2 is preheated into the prepreg of after-tack according to the machine direction of design conclusion, lay on preheating heating platform
Order is laid, and is extruded the bubble of interlayer along machine direction during lay, is finally paved into the regular carbon fiber composite of shape
The bed of material；This kind of bubble extrusion method can effectively avoid material prepreg fiber when carrying out molding processing out of shape, made
Product can guarantee that the characteristics such as its uniform, smooth, air-gap-free；
Step 4, molding processing procedure, including：
It is multiple according to PTFE release cloths, carbon fiber in membranous disc fixture after obtaining the regular carbon fibre composite layer of shape
The laying order of condensation material layer and PTFE release cloths is laid, and then, is protected membranous disc mold-locked using connection clamp system
Hold pressure；
Step 5, cure knockout course, including：
First, the mould of locking is put into baking oven, toasted at a temperature of 140 DEG C the curing course of 120min；So
Afterwards, treat that product is cooled to 20 ± 5 DEG C, the carbon fibre composite layer is demoulded；Finally, product cut, beaten
Mill and surface treatment, obtain carbon fibre composite shaping membranous disc.
Beneficial effect：
The method of the present invention specify that carbon fibre composite is molded membranous disc manufacturing process, this kind of technique has many advantages：
Product intensity and modulus is high, and density is low, higher than performance, no creep, and superhigh temperature resistant under non-oxidizing atmosphere, fatigue durability is good, and heat is swollen
Swollen coefficient is small and has anisotropy, good corrosion resistance.
The moulding process of the present invention processes manufactured composite material shaping membranous disc, and fiber content is up to more than 55%, table
Face light bubble-free, interfacial bonding strength reach the effect of die press technology for forming, realize lighter stronger purpose, can meet boat
The requirement that empty space flight navigational field produces carbon fiber composite material article.
Brief description of the drawings：
Fig. 1 is that prepreg cloth cuts processing structure schematic diagram in embodiment 1；
Fig. 2 is mold structure diagram in embodiment 1；
Fig. 3 is solidification process structure diagram in embodiment 1；
Wherein：1- prepreg cloth retractable frames, 2- vibration cutter, 3- Cutting platforms, 4- prepreg cloths；5- punch-pin, 6- molding spiral shells
Bolt, 7- positioning pins, 8- cavity plates, 9- movable wedges；10- baking ovens, the mould after 11- assemblings.
Embodiment：
Embodiment one：
The carbon fibre composite shaping membranous disc manufacturing process of present embodiment, this kind of carbon fibre composite are molded membranous disc
Manufacturing process, it is related to the cutting method of resin-based carbon fiber prepreg cloth, i.e., first by the assembling of web-like prepreg cloth on rack,
Prepreg cloth edge and position correction mechanical structure are fixed, it is multiple fingers to be cut prepreg cloth using vibrations cutter
The prepreg being sized, the prepreg cut is collected, and is repeated the above steps and is completed until all prepreg cloths are cut.
Prepreg made from the cutting method of this kind of resin-based carbon fiber prepreg cloth has thickness uniformly and accurate size, right
Compactness, uniformity, the dimensional accuracy of product have very significant raising.
This kind of carbon fibre composite is molded membranous disc manufacturing process, it is related to pre- heat working technological process, i.e., in mould
Non-contact thermal nearby is carried out to mould using heating equipment, mould is heated up from inside to outside uniformly.The heating process method
Temperature-controllable precision can reach ± 0.2 DEG C, can effectively control mold temperature and energy loss to be less than 20%.
This kind of mould preheating heating process method has the advantage that compared with traditional infrared heating：Mould be by it is interior to
Outer heating, temperature can keep stablizing and uniformly, can guarantee that interlayer gas is effectively extruded when prepreg is laid with；Non-contact thermal
Temperature control it is exactly accurate, temperature-controllable precision can reach ± 0.2 DEG C, can guarantee that the viscosity and stream of resin when being laid with
Dynamic property；Energy loss is less than 20%, and the security risk of operator is reduced during manufacturing.
This kind of carbon fibre composite is molded membranous disc manufacturing process, i.e., applies pretightning force, the carbon that will be cut out using mould
Fibrous composite prepreg, is laid according to designed machine direction, laying order, is paved into the regular carbon fiber of shape
Composite layer is positioned over mould inside, and the method for forming carbon fibre composite layer, is realized according to following steps.
The technique is realized by following steps：
Step 1, prepreg cutting processing procedure, including：The prepreg of web-like is assembled on rack, prepreg is being passed through
Paved on latitude cutting machine and calibrate spacing, debugging cutting machine, according to laying requirement and laying the difference of angle, according to cutting machine
The figure drawn is cut, and is repeated the above steps and is completed until all prepreg cloths are cut, and collects the preimpregnation cut
Material；Prepreg made from the cutting method of this kind of resin-based carbon fiber prepreg cloth has thickness uniformly and accurate size, to product
Compactness, uniformity, dimensional accuracy have very significant raising；
Step 2, membranous disc mold cleaning and prepreg warm：
First, membranous disc die surface is cleared up to free from admixture attachment state using acetone, it is then, equal in membranous disc die surface
The even epoxy resin release agent for coating 2-3 times, finally, the prepreg obtained using heating platform to step 1 cutting are preheated
Heating operation；
Step 3, prepreg laid course, including：
Step 2 is preheated into the prepreg of after-tack according to the machine direction of design conclusion, lay on preheating heating platform
Order is laid, and is extruded the bubble of interlayer along machine direction during lay, is finally paved into the regular carbon fiber composite of shape
The bed of material；This kind of bubble extrusion method can effectively avoid material prepreg fiber when carrying out molding processing out of shape, made
Product can guarantee that the characteristics such as its uniform, smooth, air-gap-free；
Step 4, molding processing procedure, including：
It is multiple according to PTFE release cloths, carbon fiber in membranous disc fixture after obtaining the regular carbon fibre composite layer of shape
The laying order of condensation material layer and PTFE release cloths is laid, and then, is protected membranous disc mold-locked using connection clamp system
Hold pressure；
Step 5, cure knockout course, including：
First, the mould of locking is put into baking oven, toasted at a temperature of 140 DEG C the curing course of 120min；So
Afterwards, treat that product is cooled to 20 ± 5 DEG C, the carbon fibre composite layer is demoulded；Finally, product cut, beaten
Mill and surface treatment, obtain carbon fibre composite shaping membranous disc.Maximum stress through the forces testing product is
172.3MPa, maximum displacement compensation are 6.7mm, and maximum angle compensation is 1.8 °.
Embodiment two：
Unlike embodiment one, the carbon fibre composite shaping membranous disc manufacturing process of present embodiment,
The figure drawn according to cutting machine described in step 1 is cut, and is repeated the above steps until all prepreg cloths have been cut
During, prepreg is carried out by cutting processing using the cutting method of coordinate cutting machine vibrations cutter.
Embodiment three：
Unlike embodiment one or two, the carbon fibre composite shaping membranous disc manufacture work of present embodiment
Skill, when the prepreg obtained using heating unit to step 1 cutting described in step 2 carries out preheating heating operation, used adds
Hot charging is set to digitlization heating platform device.
Embodiment four：
Unlike embodiment three, the carbon fibre composite shaping membranous disc manufacturing process of present embodiment,
It is that prepreg is heated to 29 ± 1 DEG C when the prepreg obtained to step 1 cutting described in step 2 carries out preheating heating operation.
Embodiment five：
Unlike embodiment one, two or four, the carbon fibre composite shaping membranous disc system of present embodiment
Make technique, in the prepreg laid course described in step 3, membranous disc mould has cavity plate and punch-pin two parts, membranous disc mould it is convex
The taper of mould is identical with the design variations amount of membranous disc.
Embodiment six：
Unlike embodiment five, the carbon fibre composite shaping membranous disc manufacturing process of present embodiment,
Prepreg described in step 3 is laid according to the machine direction of design conclusion table 2, laying order, by the gas of interlayer during lay
It is to extrude the bubble of interlayer along machine direction during bubble extrusion.
Embodiment seven：
Unlike embodiment one, two, four or six, the carbon fibre composite shaping membranous disc of present embodiment
Manufacturing process, in the prepreg laid course described in step 3, is paved into the outer contour ruler of the regular carbon fibre composite layer of shape
The very little Internal periphery size than the membranous disc mould is big 2.75mm~3.15mm.The deviation can effectively lift carbon fibre composite
Deformation and packing phenomenon of the layer in heating process is cured.
Embodiment eight：
Unlike embodiment seven, the carbon fibre composite shaping membranous disc manufacturing process of present embodiment,
In curing knockout course described in step 5, female die of die border is equipped with movable wedge, and when demoulding can utilize movable wedge by product
Ejection.
Embodiment nine：
Unlike embodiment one, two, four, six or eight, the carbon fibre composite shaping of present embodiment
Membranous disc manufacturing process, mould described in mould laying step are equipped with 4 positioning pins, 9 die bolts.
Embodiment ten：
Unlike embodiment nine, the carbon fibre composite shaping membranous disc manufacturing process of present embodiment,
In molding processing procedure described in step 4, pretightning force used is during using connection clamp system, membranous disc mold-locked is operated
95-135N.Using the pretightning force in the range of this can control resin spill-out of the mould product in the solidification process of next step with
Finished size is maintained in normal range (NR).
Embodiment 11：
Unlike embodiment one, two, four, six, eight or ten, the carbon fibre composite of present embodiment into
Type membranous disc manufacturing process, the pretightning force are 103N.
Embodiment 12：
Unlike embodiment 11, the carbon fibre composite shaping membranous disc manufacture work of present embodiment
Skill, it is described to carry out cured process according to the curing course of design using baking oven in the curing knockout course described in step 5
In, baking oven used is welded using stainless steel material, its internal internal fan makes air keep Convection states, make inside it by
It is hot uniform.
Embodiment 1：
Carbon fiber epoxy prepreg cloth is 5228 carbon of SYT700S/ epoxies of Zhongfu Shenying Carbon Fiber Limited Liability Company
Fiber prepreg, its one-way slabs mechanical property is as shown in table 1, is placed horizontally at Jingwei Systemtechnik Ltd.
On FH-RM composite industry coordinate cutting machines, installation cutting angle is 26 ° of cutting blades, and adjustment knife depth is 42.00mm, such as
Limiting devices of the Fig. 1 along fiber extending direction installation cutting equipment；And the end face of prepreg is arranged to horizontal with limiting device
Edge aligns, and wide cut prepreg cloth to be cut is entirely absorbed and fixed at the work of cutting machine by the air draught fixation for opening cutting machine
Table top；Using cutting process software positional dissection knife initial position and draw cutting path, start wide cut prepreg cutting
Work, that is, the cutting for starting prepreg tape make；Finally the prepreg after cutting is laid on shown in Fig. 2 in mould to complete the step
Suddenly.
Mould 11 in Fig. 3 is to elect No. 45 steel molds with pattern draft as, and mould is cleared up to nothing with acetone
Impurity attachment state, after being evenly applied to die surface 2-3 times using epoxy resin release agent afterwards, mould is heated to
29℃±1℃。
After prepreg is carried out pre- thermal softening, prepreg is laid according to machine direction, the laying order of table 2, is spread
If when every layer all the bubble of fiber interlayer is extruded with scraper plate, be paved into the regular carbon fibre composite layer of shape.
It is laid with and stops heating when completing, carbon fibre composite layer, the PTFE completed according to PTFE release cloths, lay is demoulded
The order of cloth is laid to mould, is locked mould with the pretightning force of 103N using connection clamp system.
Start and debug baking oven, set it is corresponding cure course, by the mould of locking be put into baking oven with 140 DEG C/
120min is curing course；After curing after mould is cooled to room temperature, the carbon fibre composite layer is demoulded；
Cutting polishing is carried out to product, is surface-treated, obtains carbon fibre composite shaping membranous disc.Through the forces testing product
Maximum stress is 172.3MPa, and maximum displacement compensation is 6.7mm, and maximum angle compensation is 1.8 °.
Table 1, one-way slabs mechanical property：
| Longitudinal tensile strength | 1910MPa | Longitudinal tensile | 130GPa |
| Longitudinal compressive strength | 1154MPa | Cross directional stretch modulus | 10.3GPa |
| Transverse tensile strength | 22MPa | In-plane Shear Modulus | 4.7GPa |
| Transverse compression intensity | 150MPa | Poisson's ratio | 0.3 |
| Shear strength | 79MPa |
Table 2, machine direction, laying order of the prepreg according to table 2, design parameter requires designed and actual use：
Claims (10)
1. a kind of carbon fibre composite is molded membranous disc manufacturing process, it is characterized in that：The technique is realized by following steps：
Step 1, prepreg cutting processing procedure, including：The prepreg of web-like is assembled on rack, prepreg is cut in longitude and latitude
Paved on cutting mill and calibrate spacing, debugging cutting machine, according to laying requirement and laying the difference of angle, painted according to cutting machine
The figure of system is cut, and is repeated the above steps and is completed until all prepreg cloths are cut, and collects the prepreg cut；
Step 2, membranous disc mold cleaning and prepreg warm：
First, membranous disc die surface is cleared up to free from admixture attachment state using acetone, then, is uniformly applied in membranous disc die surface
The epoxy resin release agent of 2-3 times is covered, finally, the prepreg obtained using heating platform to step 1 cutting carries out preheating heating
Operation；
Step 3, prepreg laid course, including：
Step 2 is preheated to the prepreg of after-tack on preheating heating platform according to machine direction, the laying order for designing conclusion
Laid, the bubble of interlayer is extruded along machine direction during lay, be finally paved into the regular carbon fibre composite layer of shape；
Step 4, molding processing procedure, including：
After obtaining the regular carbon fibre composite layer of shape, according to PTFE release cloths, carbon fiber composite in membranous disc fixture
The laying order of the bed of material and PTFE release cloths is laid, and then, keeps pressing by membranous disc mold-locked using connection clamp system
Power；
Step 5, cure knockout course, including：
First, the mould of locking is put into baking oven, toasted at a temperature of 140 DEG C the curing course of 120min；Then, treat
Product is cooled to 20 ± 5 DEG C, and the carbon fibre composite layer is demoulded；Finally, product is cut, polish and
Surface treatment, obtains carbon fibre composite shaping membranous disc.
2. carbon fibre composite according to claim 1 is molded membranous disc manufacturing process, it is characterised in that：Described in step 1
The figure drawn according to cutting machine cut, repeat the above steps until by all prepreg cloths cutting complete process
In, prepreg is carried out by cutting processing using the cutting method of coordinate cutting machine vibrations cutter.
3. carbon fibre composite according to claim 1 or 2 is molded membranous disc manufacturing process, it is characterised in that：Step 2 institute
When the prepreg obtained using heating unit to step 1 cutting stated carries out preheating heating operation, heating unit used is number
Word heating platform device.
4. carbon fibre composite according to claim 3 is molded membranous disc manufacturing process, it is characterised in that：Described in step 2
When carrying out preheating heating operation to the obtained prepreg of step 1 cutting, be that prepreg is heated to 29 ± 1 DEG C.
5. the carbon fibre composite shaping membranous disc manufacturing process according to claim 1,2 or 4, it is characterised in that：Step 3
In the prepreg laid course, membranous disc mould has cavity plate and punch-pin two parts, the taper and film of the punch-pin of membranous disc mould
The design variations amount of disk is identical.
6. carbon fibre composite according to claim 5 is molded membranous disc manufacturing process, it is characterised in that：Described in step 3
Prepreg laid according to the design machine direction of conclusion, laying order, the process that when lay extrudes the bubble of interlayer
In, it is to extrude the bubble of interlayer along machine direction.
7. the carbon fibre composite shaping membranous disc manufacturing process according to claim 1,2,4 or 6, it is characterised in that：Step
In prepreg laid course described in rapid 3, the outer profile size of the regular carbon fibre composite layer of shape is paved into than the film
Big 2.75mm~the 3.15mm of Internal periphery size of disk mould.
8. carbon fibre composite according to claim 7 is molded membranous disc manufacturing process, it is characterised in that：Described in step 4
Molding processing procedure in, pretightning force used is 95-135N during using connection clamp system, membranous disc mold-locked is operated.
9. carbon fibre composite according to claim 8 is molded membranous disc manufacturing process, it is characterised in that：The pretightning force
For 103N.
10. the carbon fibre composite shaping membranous disc manufacturing process according to claim 1,2,4,6,8 or 9, its feature exist
In：It is described to carry out cured process according to the curing course of design using baking oven in curing knockout course described in step 5
In, baking oven used is welded using stainless steel material, its internal internal fan makes air keep Convection states, make inside it by
It is hot uniform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711234088.3A CN108016054A (en) | 2017-11-20 | 2017-11-20 | Carbon fibre composite is molded membranous disc manufacturing process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711234088.3A CN108016054A (en) | 2017-11-20 | 2017-11-20 | Carbon fibre composite is molded membranous disc manufacturing process |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108016054A true CN108016054A (en) | 2018-05-11 |
Family
ID=62077641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711234088.3A Pending CN108016054A (en) | 2017-11-20 | 2017-11-20 | Carbon fibre composite is molded membranous disc manufacturing process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108016054A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109318507A (en) * | 2018-10-23 | 2019-02-12 | 西安康本材料有限公司 | A kind of big L/D ratio carbon fibre reinforced pipe production mold and forming method |
| CN112092413A (en) * | 2020-09-29 | 2020-12-18 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flexible carbon nanotube film self-heating platform and method for assisting in automatic laying |
| CN112210192A (en) * | 2020-10-30 | 2021-01-12 | 大连交通大学 | Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof |
| CN112757663A (en) * | 2020-12-31 | 2021-05-07 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Automatic filament-laying forming method for continuous fiber reinforced thermoplastic composite material |
| CN112848371A (en) * | 2020-12-31 | 2021-05-28 | 安徽佳力奇先进复合材料科技股份公司 | Preparation process of carbon fiber composite rib |
| CN112873902A (en) * | 2020-12-31 | 2021-06-01 | 浙江恒源洁具股份有限公司 | Carbon fiber integrated basin and preparation process thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000263658A (en) * | 1999-03-18 | 2000-09-26 | Toray Ind Inc | Power transmission member made of fiber-reinforced composite material |
| CN1944527A (en) * | 2002-11-28 | 2007-04-11 | 三菱丽阳株式会社 | Epoxy resin for prepreg, prepreg, fiber-reinforced composite material, and processes for producing same |
| CN201141405Y (en) * | 2007-12-25 | 2008-10-29 | 中国船舶重工集团公司第七一一研究所 | Flexible connection element |
| CN103881176A (en) * | 2012-12-20 | 2014-06-25 | 辽宁辽杰科技有限公司 | High-strength continuous fiber reinforced thermoplastic sheet material, preparation method and application thereof |
| EP2762741A2 (en) * | 2013-01-30 | 2014-08-06 | Technische Universität Darmstadt | Membrane coupling |
| CN107214980A (en) * | 2017-06-27 | 2017-09-29 | 东莞市海旭新材料技术有限公司 | A kind of quick molding method of thermoplastic fiber reinforced composite board |
-
2017
- 2017-11-20 CN CN201711234088.3A patent/CN108016054A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000263658A (en) * | 1999-03-18 | 2000-09-26 | Toray Ind Inc | Power transmission member made of fiber-reinforced composite material |
| CN1944527A (en) * | 2002-11-28 | 2007-04-11 | 三菱丽阳株式会社 | Epoxy resin for prepreg, prepreg, fiber-reinforced composite material, and processes for producing same |
| CN201141405Y (en) * | 2007-12-25 | 2008-10-29 | 中国船舶重工集团公司第七一一研究所 | Flexible connection element |
| CN103881176A (en) * | 2012-12-20 | 2014-06-25 | 辽宁辽杰科技有限公司 | High-strength continuous fiber reinforced thermoplastic sheet material, preparation method and application thereof |
| EP2762741A2 (en) * | 2013-01-30 | 2014-08-06 | Technische Universität Darmstadt | Membrane coupling |
| CN107214980A (en) * | 2017-06-27 | 2017-09-29 | 东莞市海旭新材料技术有限公司 | A kind of quick molding method of thermoplastic fiber reinforced composite board |
Non-Patent Citations (2)
| Title |
|---|
| 吴桔生: "《电涡流技术与应用》", 31 August 2014, 中南大学出版社 * |
| 胡玉洁: "《材料加工原理及工艺学 聚合物材料分册》", 30 April 2017, 哈尔滨工业大学出版社 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109318507A (en) * | 2018-10-23 | 2019-02-12 | 西安康本材料有限公司 | A kind of big L/D ratio carbon fibre reinforced pipe production mold and forming method |
| CN112092413A (en) * | 2020-09-29 | 2020-12-18 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flexible carbon nanotube film self-heating platform and method for assisting in automatic laying |
| CN112092413B (en) * | 2020-09-29 | 2024-04-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Self-heating platform and method for auxiliary automatic laying flexible carbon nanotube film |
| CN112210192A (en) * | 2020-10-30 | 2021-01-12 | 大连交通大学 | Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof |
| CN112210192B (en) * | 2020-10-30 | 2022-06-10 | 大连交通大学 | Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof |
| CN112757663A (en) * | 2020-12-31 | 2021-05-07 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Automatic filament-laying forming method for continuous fiber reinforced thermoplastic composite material |
| CN112848371A (en) * | 2020-12-31 | 2021-05-28 | 安徽佳力奇先进复合材料科技股份公司 | Preparation process of carbon fiber composite rib |
| CN112873902A (en) * | 2020-12-31 | 2021-06-01 | 浙江恒源洁具股份有限公司 | Carbon fiber integrated basin and preparation process thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108016054A (en) | Carbon fibre composite is molded membranous disc manufacturing process | |
| CA2823765C (en) | Method and apparatus for resin transfer molding composite parts | |
| CN110103488B (en) | Continuous die pressing manufacturing process of fan blade thermoplastic composite material beam cap | |
| CN110815856A (en) | Soft die manufacturing method for forming I-beam composite material part and application thereof | |
| JP2009542483A (en) | Manufacturing method of composite parts | |
| CN102105296A (en) | Device and method for the manufacture of three dimensional beam type elements in composite material | |
| CN102320144A (en) | Manufacture die for carbon fiber composite integrative multipass joint and preparation method thereof | |
| WO2019188195A1 (en) | Method for producing fiber-reinforced resin | |
| CN105269833A (en) | Two-time compression molding technology for thermoplastic composite material | |
| WO2019149010A1 (en) | Molding method of composite material member and composite material member | |
| CN111716761A (en) | Special-shaped curved surface aramid fiber paper honeycomb simple pre-setting die and manufacturing method thereof | |
| CN111113943A (en) | C-shaped beam forming method and C-shaped beam | |
| CN112454950A (en) | Technological skin, wave-absorbing composite material part and preparation method thereof | |
| CN110561782A (en) | Composite material secondary curing molding method based on internal grid rib structure and application | |
| CN108215242B (en) | Forming method of resin-based composite material | |
| EP2428589A2 (en) | Method for producing a laying mould for producing components | |
| CN112829334B (en) | Variable-thickness heat-proof layer, variable-thickness heat-proof layer forming die and forming method | |
| KR101536670B1 (en) | radome for antenna and manufacturing method thereof | |
| CN110815853A (en) | Forming method and application of air bag die for forming composite J-shaped beam | |
| CN114379110B (en) | Split-mold paving self-adaptive soft mold forming method for super-thickness variable-curvature composite material part | |
| JP6712430B1 (en) | Method for producing thermoplastic fiber-reinforced resin molded product | |
| CN212603540U (en) | Simple pre-setting die for aramid fiber paper honeycomb with special-shaped curved surface | |
| CN109094057A (en) | A kind of carbon fiber automobile front chamber lid compression-moulding methods | |
| CN111690235B (en) | Skin mold forming material and manufacturing and application thereof | |
| CN117429598B (en) | Special-shaped reinforced rigidity-variable composite material structure and forming method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180511 |
|
| RJ01 | Rejection of invention patent application after publication |