CN103273662A - Preparation method of low heat expansion carbon fiber reinforced resin matrix composite material mold - Google Patents
Preparation method of low heat expansion carbon fiber reinforced resin matrix composite material mold Download PDFInfo
- Publication number
- CN103273662A CN103273662A CN2013101968922A CN201310196892A CN103273662A CN 103273662 A CN103273662 A CN 103273662A CN 2013101968922 A CN2013101968922 A CN 2013101968922A CN 201310196892 A CN201310196892 A CN 201310196892A CN 103273662 A CN103273662 A CN 103273662A
- Authority
- CN
- China
- Prior art keywords
- mould
- profile
- carbon fiber
- composite material
- preparation
- 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.)
- Granted
Links
Images
Landscapes
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to a preparation method of a low heat expansion carbon fiber reinforced resin matrix composite material mold, belonging to the technical field of composite material preparation. The method is capable of forming a molding surface with a VARI (Vacuum Assisted Resin Infusion) technique, and ensuring low heat expansion performance of the mold by controlling the carbon fiber laying direction, precuring temperature, postcuring manner and postprocessing manner of the molding surface. With the adoption of the VARI technique, when a vacuum pressure reaches to 0.1MPa, carbon fiber cloth is compressed by vacuum, so that the product is internally dense after resin is guided in the product, and the volume content of composite material fibers is ensured; and meanwhile, bubbles between carbon fiber cloth layers are removed so as to ensure that the content of internal pores of the composite material is as few as possible and ensure the strength of the composite material.
Description
Technical field
The present invention relates to the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould, belong to the Composite Preparation technical field.
Background technology
Composite is because of its excellent material property and operational characteristic, at main force support structures such as aircraft wing, fuselage, central wing boxes, obtained extensive use above the carrier rocket on the space structure spares such as level, satellite bearing cylinder, satellite battery battle array, missile case, but application scale and aspects such as level, manufacturing process and equipment in China still far lag behind developed country, especially composite material mould does not also obtain promoting at home, and composite material mould has all obtained extensive use at aerospace field in American-European developed country.
At present domestic when making the composite product of high-performance, high-precision requirement, still at first select cast aluminium or mild steel frock, mold weight is big, the manufacturing cycle is long, but the high toolability of thermal capacity is poor, thermal coefficient of expansion and composite difference are big, brings problems for the production of composite product.And the composite material mould quality is light, is easy to carrying, and the manufacturing cycle is short, thermal capacity is low, uniformity of temperature profile, but toolability is good, especially thermal coefficient of expansion and composite product are complementary, and can solve the scale error and the curing deformation problem that perplex composite product all the time.
Owing to be subjected to restrictions such as perfusion resin system temperature tolerance, impact resistance, make composite material mould in the document both domestic and external and adopt the carbon fiber prepreg autoclave forming process more, rarely have employing vacuum aided (VARI) technology to make the report of composite material mould, especially domestic late to the starting of VARI technical study, carry out the research of VARI forming composite mould still less.
Summary of the invention
The objective of the invention is big for the quality that solves metal die, the production cycle long, thermal coefficient of expansion and the unmatched problem of composite, the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould is proposed, prepared composite material mould specific strength height, the high and low thermal expansion of specific stiffness, manufacturing cycle weak point, antifatigue, corrosion-resistant, quality gently and the fail safety performance good.
The objective of the invention is to be achieved through the following technical solutions.
The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould of the present invention, this method VARI technological forming profile, and by control profile carbon fiber shop layer direction, precuring temperature, back curing mode and post processing mode, guarantee mould low-thermal-expansion performance; Low-thermal-expansion carbon fiber enhancement resin base composite material mould is hereinafter to be referred as this mould; Concrete implementation step is:
The first step, design this mould structure:
Molding surface size according to product designs this mould structure, takes into full account the product technology conditional request, guarantees the smooth demoulding of product, makes mould have good ventilation, heat-transfer effect, reduces mold weight as far as possible under the prerequisite that guarantees mold stiffness;
In second step, design the profile of this mould and spread layer:
According to Classical lamination theory design shop layer angle and order, make the thermal coefficient of expansion of this mould satisfy product to the performance requirement of low bulk mould;
The 3rd step, the profile moulding of this mould:
A3.1, making master mold: profile and moulding process according to product are made master mold;
The profile moulding of A3.2, this mould: the shop layer angle and the order lay carbon fiber that design according to second step on the master mold surface that A3.1 makes, lay permeable medium at carbon fiber surface, coat vacuum bag, utilize vacuum perfusion process to soak into carbon fiber with resin, and the precuring moulding;
Solidify behind A3.3, this die face and handle, make the material heat endurance satisfy instructions for use.
The 4th goes on foot, and makes the support frame of this mould: according to first step mould structure design support frame structure form, adopt metal material or composite to make support frame;
The 5th step, profile and the 4th support frame that goes on foot making that the 3rd step made are assembled: support frame is installed at the back side at this mould, as select for use the metal framework mounting means for flexibly connecting, and making framework as adopting the composite identical with the profile thermal coefficient of expansion, can directly be adhesively fixed;
The 6th step, the profile post processing of this mould:
Follow the tracks of detector with three-dimensional laser and detect this mould and die accuracy, confirm the profile changing value of this mould; When the profile of this mould changes hour, utilize the polishing grinding treatment process, the profile of this mould is adhered to specification; Overproof when big when the molding surface size of this mould, utilize the profile of this mould of five-shaft numerical control Cutter Body Processing with Machining Center, and the profile of this mould after the processing is carried out polishing, guarantee that mold surface finish meets design requirement.
In the described steps A 3.2 employed carbon fiber woven cloth specification be ± 45 ° of twin shafts to, 0 °/± 45 ° three axially or 0 ° of single shaft to or use wherein two kinds of specifications or all uses of three kinds of specifications;
VARI technology is adopted in the profile moulding of described steps A 3.2 these moulds, and formed product pressure is 0.08～0.1MPa, and the composite fiber volume content is 50%～55% after the moulding, and properties of product are stable;
Cold curing technology is adopted in the profile precuring of described steps A 3.2 these moulds, and room temperature precuring can guarantee that thermal deformation does not take place master mold, guarantees the die face dimensional accuracy.
The present invention compared with prior art beneficial effect is:
(1) VARI technology, when the pneumatics power of taking seriously reaches 0.1MPa, vacuum is carried out compacting with carbon fiber cloth makes product inside, resin importing back closely knit, guarantee the composite fiber volume content, remove carbon fiber cloth interlayer bubble simultaneously, guarantee that the composite inner voids content is the least possible, guarantee composite material strength.
(2) arrange and grammes per square metre by changing the fiber different directions, the linear expansion coefficient of designing mould different directions is complementary the thermal expansion of itself and target composite product.
(3) the carbon fibre composite die face is at the master mold surface forming, general master mold material mostly is the higher epoxy of thermal coefficient of expansion for wood gum, as directly heating cure in the profile forming process, then can take place influences the final profile precision of mould because of the case mold facial disfigurement.The present invention designs and adopts room temperature precuring technology, avoids taking place to influence because of the master mold thermal deformation problem of the final molding surface size of composite material mould.
(4) the precuring die face be put in the tun heat, make in the mould last handling process the temperature field evenly, stable, and by heat medium die surface is heated evenly, avoid local heating to produce internal stress, cause the mould local deformation.
Description of drawings
Fig. 1 is the profile schematic diagram of master mold;
Fig. 2 is the profile schematic diagram of this mould of the present invention.
The specific embodiment
Embodiment 1
The example of made is the required moulds of the parabolic goods of a kind of moulding high accuracy dimensional requirement carbon fiber, and parabolic area diameter projected is 0.9m, and profile is irregular surface.Require the long-term serviceability temperature of mould to be higher than 150 ℃, mold materials linear expansion coefficient in the time of 150 ℃ is not more than 4 * 10
-6/ K.
The first step, design this mould structure:
On the peripheral 100mm technology limit that increases of goods, make vacuum bag when being used for the composite products moulding, the die shape structure is as shown in Figure 2.And designing mould moulding master mold, master mold is die, with die face after the assurance moulding;
In second step, design the profile of this mould and spread layer: require to be not more than 4 * 10 according to the mold hot coefficient of expansion
-6/ K, by the finite element analysis modeling, design profile shop layer structure is [0 °/60 °/-60 °]
20, mould shop, layer back, analytical calculation shop layer structural composite material thermal coefficient of expansion is 3.5 * 10
-6/ K;
The 3rd step, the profile moulding of this mould:
A3.1, making master mold: according to first step design master mold profile, adopt glass fiber reinforced plastics composite material to make the product master mold; The profile of master mold as shown in Figure 1;
The profile moulding of A3.2, this mould: the shop layer angle and the order lay carbon fiber that design according to second step on the master mold surface that A3.1 makes, lay release cloth, porose barrier film, water conservancy diversion net at carbon fiber surface, coat vacuum bag, utilize vacuum perfusion process to soak into carbon fiber with epoxy resin, and the precuring moulding;
A3.3, precuring finished after the die face demoulding, the back of heating under 150 ℃ is solidified and is handled 8h, makes the material heat endurance satisfy instructions for use.
The 4th goes on foot, and makes the support frame of this mould: adopt shop layer structure and the material system identical with die face, make the mould support frame according to the method for A3.2.
In the 5th step, the support frame that the profile that the 3rd step was made and the 4th step make is assembled: namely the concave surface of this mould is installed support frame at the back side of this mould, and mounting means is for glueing joint;
The 6th step, the profile post processing of this mould:
Detect this mould and die accuracy with the three-dimensional laser tracker, confirm the profile precision of this mould; This die face accuracy error satisfies instructions for use less than ± 0.15mm after the detection.
Employed carbon fiber woven cloth specification is 0 ° of single shaft fabric in the described steps A 3.2, and the carbon fiber woven cloth surface density is 200g/m
2
VARI technology is adopted in the profile moulding of described steps A 3.2 these moulds, and formed product pressure is 0.08～0.1MPa, and the composite fiber volume content is 50%～55% after the moulding, and properties of product are stable;
Cold curing technology is adopted in the profile precuring of described steps A 3.2 these moulds, and room temperature precuring can guarantee that thermal deformation does not take place master mold, guarantees the die face dimensional accuracy;
Described steps A 3.2 these epoxy resin are selected bisphenol A type epoxy resin for use.The shop layer is made 300mm * 300mm carbon fiber enhancement resin base composite material plate according to shop layer mould ply sequence.Under room temperature～150 ℃, the horizontal average coefficient of linear expansion of this sheet material is 3.48 * 10
-6/ K.
Curing process is for to be placed on die face in the tun after the profile of described steps A 3.3 these moulds, all be coated and fixed with heat-conducting medium (thermal conductive sand or glass microballoon) around the profile, heat then and do back curing, improve the composite material solidification degree, reach mould and use the heatproof requirement.
Claims (7)
1. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould is characterized in that steps of the method are:
The first step, design this mould structure:
Molding surface size according to product designs this mould structure;
In second step, design the profile of this mould and spread layer:
According to Classical lamination theory design shop layer angle and order;
The 3rd step, the profile moulding of this mould:
A3.1, making master mold: profile and moulding process according to product are made master mold;
The profile moulding of A3.2, this mould: the shop layer angle and the order lay carbon fiber that design according to second step on the master mold surface that A3.1 makes, lay permeable medium at carbon fiber surface, coat vacuum bag, utilize vacuum perfusion process to soak into carbon fiber with resin, and the precuring moulding;
Solidify behind A3.3, this die face and handle;
The 4th goes on foot, and makes the support frame of this mould: according to first step mould structure design support frame structure form;
In the 5th step, profile and the 4th support frame that goes on foot making that the 3rd step made are assembled: support frame is installed at the back side at this mould;
In the 6th step, the preparation of this mould is finished in the profile post processing of this mould.
2. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould according to claim 1, it is characterized in that: support frame is metal material, the connected mode of the profile that metal framework and the 3rd step make is for flexibly connecting.
3. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould according to claim 1, it is characterized in that: support frame is the composite identical with the profile thermal coefficient of expansion, with the connected mode of profile for directly bonding.
4. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould according to claim 1 is characterized in that: in the steps A 3.2 employed carbon fiber woven cloth specification for ± 45 ° of twin shafts to, 0 °/± 45 ° three axially or 0 ° of single shaft to or use wherein two kinds of specifications or all uses of three kinds of specifications.
5. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould according to claim 1, it is characterized in that: VARI technology is adopted in the profile moulding of steps A 3.2 these moulds, formed product pressure is 0.08～0.1MPa, and the composite fiber volume content is 50%～55% after the moulding.
6. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould according to claim 1 is characterized in that: the profile precuring employing cold curing technology of steps A 3.2 these moulds.
7. the preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould according to claim 1, it is characterized in that: the last handling process in the 6th step is: follow the tracks of detector with three-dimensional laser and detect this mould and die accuracy, confirm the profile changing value of this mould; When the profile of this mould changes hour, utilize the polishing grinding treatment process, the profile of this mould is adhered to specification; Overproof when big when the molding surface size of this mould, utilize the profile of this mould of five-shaft numerical control Cutter Body Processing with Machining Center, and the profile of this mould after the processing is carried out polishing, guarantee that mold surface finish meets design requirement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310196892.2A CN103273662B (en) | 2013-05-24 | 2013-05-24 | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310196892.2A CN103273662B (en) | 2013-05-24 | 2013-05-24 | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103273662A true CN103273662A (en) | 2013-09-04 |
| CN103273662B CN103273662B (en) | 2016-03-30 |
Family
ID=49056333
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310196892.2A Active CN103273662B (en) | 2013-05-24 | 2013-05-24 | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103273662B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104385625A (en) * | 2014-09-30 | 2015-03-04 | 北京空间机电研究所 | Composite material thin-wall housing preparation method based on unloading hole |
| CN104772912A (en) * | 2014-12-30 | 2015-07-15 | 中国兵器工业集团第五三研究所 | Method for improving interlamination strength of reinforced resin-based composite material of flat fabric |
| CN104890254A (en) * | 2014-03-06 | 2015-09-09 | 西门子公司 | A method for manufacturing a component for a wind turbine |
| CN105058814A (en) * | 2015-08-03 | 2015-11-18 | 沈阳闪宁科技有限公司 | Method for manufacturing carbon fiber resin matrix composite |
| CN105479768A (en) * | 2015-11-23 | 2016-04-13 | 西北工业大学 | Self-resistance electric heating curing method for resin-based carbon fiber composite material |
| CN105666769A (en) * | 2016-02-01 | 2016-06-15 | 江苏优培德复合材料有限公司 | One-step compression molding method for complex-molded part made of short carbon fiber sheet material |
| CN105690797A (en) * | 2016-04-07 | 2016-06-22 | 山东英特力新材料有限公司 | Preparation method of composite bed board |
| CN106553290A (en) * | 2016-11-30 | 2017-04-05 | 江西洪都航空工业集团有限责任公司 | A kind of high-precision reflector composite shaping moudle structure and its moulding technique |
| CN106985413A (en) * | 2017-04-13 | 2017-07-28 | 中航复合材料有限责任公司 | A kind of forming frock for foam core filled composite material structure winglet |
| CN108526831A (en) * | 2018-03-19 | 2018-09-14 | 中国南方航空股份有限公司 | A kind of anti-manufacture craft for being bulldozed sliding door exterior skin and repairing mold of aircraft |
| CN108656410A (en) * | 2018-05-03 | 2018-10-16 | 上海晋飞碳纤科技股份有限公司 | A kind of large mold being integrally formed labyrinth |
| CN108656579A (en) * | 2018-05-10 | 2018-10-16 | 田晓沙 | The manufacturing process of Tg120 degree or more of high-temperature composite material mold |
| CN110962364A (en) * | 2019-11-29 | 2020-04-07 | 浙江大学 | Bionic composite material spiral laying layer design method |
| CN113442339A (en) * | 2021-06-28 | 2021-09-28 | 上海交通大学 | Carbon fiber composite material die |
| CN114474508A (en) * | 2022-01-20 | 2022-05-13 | 上海酷鹰机器人科技有限公司 | Surface treatment method for composite material die |
| CN116061466A (en) * | 2023-03-07 | 2023-05-05 | 江苏新扬新材料股份有限公司 | Manufacturing method and using method of composite material die tool |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101628481A (en) * | 2009-06-01 | 2010-01-20 | 中国航空工业集团公司北京航空制造工程研究所 | Forming mould of large-sized composite material-made reinforcing wall plate by vacuum assisted resin infusion |
| CN101716654A (en) * | 2009-12-15 | 2010-06-02 | 宁夏长城须崎铸造有限公司 | New process method for manufacturing mold capable of ensuring size accuracy of cast blade for large-scale water turbine |
| CN102430712A (en) * | 2011-12-13 | 2012-05-02 | 宁夏共享集团有限责任公司 | Manufacturing method of space complex curved surface core box mold |
| EP2481558A1 (en) * | 2011-01-31 | 2012-08-01 | Eurocopter Deutschland GmbH | Device and method for manufacturing of preimpregnated preform and multi-layer preimpregnated preform resulting from said method |
| CN102909870A (en) * | 2011-08-04 | 2013-02-06 | 大连元盛科技开发有限公司 | Novel carbon fiber composite mold |
| CN102990944A (en) * | 2012-11-16 | 2013-03-27 | 中国航空工业集团公司北京航空材料研究院 | Composite material vacuum bag forming method |
-
2013
- 2013-05-24 CN CN201310196892.2A patent/CN103273662B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101628481A (en) * | 2009-06-01 | 2010-01-20 | 中国航空工业集团公司北京航空制造工程研究所 | Forming mould of large-sized composite material-made reinforcing wall plate by vacuum assisted resin infusion |
| CN101716654A (en) * | 2009-12-15 | 2010-06-02 | 宁夏长城须崎铸造有限公司 | New process method for manufacturing mold capable of ensuring size accuracy of cast blade for large-scale water turbine |
| EP2481558A1 (en) * | 2011-01-31 | 2012-08-01 | Eurocopter Deutschland GmbH | Device and method for manufacturing of preimpregnated preform and multi-layer preimpregnated preform resulting from said method |
| CN102909870A (en) * | 2011-08-04 | 2013-02-06 | 大连元盛科技开发有限公司 | Novel carbon fiber composite mold |
| CN102430712A (en) * | 2011-12-13 | 2012-05-02 | 宁夏共享集团有限责任公司 | Manufacturing method of space complex curved surface core box mold |
| CN102990944A (en) * | 2012-11-16 | 2013-03-27 | 中国航空工业集团公司北京航空材料研究院 | Composite material vacuum bag forming method |
Non-Patent Citations (2)
| Title |
|---|
| 乌云其其格 等: "高性能复合材料成型用模具材料", 《玻璃钢/复合材料》 * |
| 赵渠森: "先进复合材料及其应用", 《航空制造技术》 * |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890254A (en) * | 2014-03-06 | 2015-09-09 | 西门子公司 | A method for manufacturing a component for a wind turbine |
| US10882226B2 (en) | 2014-03-06 | 2021-01-05 | Siemens Gamesa Renewable Energy A/S | Method for manufacturing a component for a wind turbine |
| CN104890254B (en) * | 2014-03-06 | 2020-04-21 | 西门子歌美飒可再生能源公司 | Method for manufacturing a component of a wind turbine |
| CN104385625A (en) * | 2014-09-30 | 2015-03-04 | 北京空间机电研究所 | Composite material thin-wall housing preparation method based on unloading hole |
| CN104772912A (en) * | 2014-12-30 | 2015-07-15 | 中国兵器工业集团第五三研究所 | Method for improving interlamination strength of reinforced resin-based composite material of flat fabric |
| CN104772912B (en) * | 2014-12-30 | 2017-03-22 | 中国兵器工业集团第五三研究所 | Method for improving interlamination strength of reinforced resin-based composite material of flat fabric |
| CN105058814A (en) * | 2015-08-03 | 2015-11-18 | 沈阳闪宁科技有限公司 | Method for manufacturing carbon fiber resin matrix composite |
| CN105479768B (en) * | 2015-11-23 | 2018-03-27 | 西北工业大学 | The resistance electrical heating curing certainly of resin-based carbon fiber composite |
| CN105479768A (en) * | 2015-11-23 | 2016-04-13 | 西北工业大学 | Self-resistance electric heating curing method for resin-based carbon fiber composite material |
| CN105666769A (en) * | 2016-02-01 | 2016-06-15 | 江苏优培德复合材料有限公司 | One-step compression molding method for complex-molded part made of short carbon fiber sheet material |
| CN105690797A (en) * | 2016-04-07 | 2016-06-22 | 山东英特力新材料有限公司 | Preparation method of composite bed board |
| CN106553290A (en) * | 2016-11-30 | 2017-04-05 | 江西洪都航空工业集团有限责任公司 | A kind of high-precision reflector composite shaping moudle structure and its moulding technique |
| CN106985413A (en) * | 2017-04-13 | 2017-07-28 | 中航复合材料有限责任公司 | A kind of forming frock for foam core filled composite material structure winglet |
| CN106985413B (en) * | 2017-04-13 | 2019-05-14 | 中航复合材料有限责任公司 | A kind of forming frock for foam core filled composite material structure winglet |
| CN108526831A (en) * | 2018-03-19 | 2018-09-14 | 中国南方航空股份有限公司 | A kind of anti-manufacture craft for being bulldozed sliding door exterior skin and repairing mold of aircraft |
| CN108656410A (en) * | 2018-05-03 | 2018-10-16 | 上海晋飞碳纤科技股份有限公司 | A kind of large mold being integrally formed labyrinth |
| CN108656579A (en) * | 2018-05-10 | 2018-10-16 | 田晓沙 | The manufacturing process of Tg120 degree or more of high-temperature composite material mold |
| CN110962364A (en) * | 2019-11-29 | 2020-04-07 | 浙江大学 | Bionic composite material spiral laying layer design method |
| CN110962364B (en) * | 2019-11-29 | 2021-03-26 | 浙江大学 | Bionic composite material spiral laying layer design method |
| CN113442339A (en) * | 2021-06-28 | 2021-09-28 | 上海交通大学 | Carbon fiber composite material die |
| CN114474508A (en) * | 2022-01-20 | 2022-05-13 | 上海酷鹰机器人科技有限公司 | Surface treatment method for composite material die |
| CN114474508B (en) * | 2022-01-20 | 2023-10-20 | 上海酷鹰机器人科技有限公司 | Surface treatment method of composite material mold |
| CN116061466A (en) * | 2023-03-07 | 2023-05-05 | 江苏新扬新材料股份有限公司 | Manufacturing method and using method of composite material die tool |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103273662B (en) | 2016-03-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103273662B (en) | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould | |
| CN107215039B (en) | Sandwich composite material and preparation method thereof | |
| CN102320139B (en) | Forming process of curved composite tube | |
| CN103407175B (en) | A kind of integral forming method of fiber-reinforced resin matrix compound material wing box | |
| CN104162994B (en) | A kind of manufacture method of carbon fiber parabola antenna | |
| CN107032658B (en) | Carbon fiber composite material and preparation method thereof | |
| Kunc et al. | Large scale additively manufactured tooling for composites | |
| CN102729482B (en) | Composite heatproof bearing cylinder and preparation method thereof | |
| CN103538715B (en) | A kind of matrix material �� type ear blade terminal and overall curing molding method altogether thereof | |
| CN102990944B (en) | Composite material vacuum bag forming method | |
| CN104162996B (en) | The manufacturing process of the U-shaped part of carbon fibre composite | |
| CN104999672B (en) | A kind of hyperbolicity variable-section variable thickness leads to the forming method of beam | |
| CN106019436B (en) | A kind of optical system full carbon fiber composite material reflector and manufacturing method | |
| CN106626438A (en) | Carbon fiber honeycomb core supporting structure and preparation method thereof | |
| CN103560332B (en) | A kind of manufacture method of caliber high-precision composite antenna surface | |
| CN103991225B (en) | The curing of three dimensional separation disjunctor reinforced resin based composites and the micro-wave oven of solidification | |
| CN106671557A (en) | Molding method of aramid fiber composite material frequency selection surface reflector | |
| CN103921453A (en) | Mold closing hydraulic assisted prepreg molding process method | |
| CN105459474A (en) | Low-density and high-performance composite sandwich structure and preparation method thereof | |
| CN103213287A (en) | Preparation method of composite material missile wing | |
| CN105034410A (en) | Vacuum compression molding device for carbon fiber composite | |
| CN104742382A (en) | Pressure-assisted VARI (vacuum assisted resin infusion) forming device and method | |
| CN108437490A (en) | A kind of carbon fibre composite skylight reinforcement plate producing process | |
| CN104690983A (en) | Method for manufacturing multi-beam parabolic antenna | |
| CN109335028A (en) | A kind of mars exploration landing rover solar heat protection outsole and its molding, assembly method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |