CN103395156A - Production process of aircraft made from carbon fiber composite material with steps at inner wall of shell - Google Patents
Production process of aircraft made from carbon fiber composite material with steps at inner wall of shell Download PDFInfo
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- CN103395156A CN103395156A CN2013103028470A CN201310302847A CN103395156A CN 103395156 A CN103395156 A CN 103395156A CN 2013103028470 A CN2013103028470 A CN 2013103028470A CN 201310302847 A CN201310302847 A CN 201310302847A CN 103395156 A CN103395156 A CN 103395156A
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- silica gel
- inner container
- aircraft
- gel inner
- mould
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- 239000002131 composite material Substances 0.000 title claims abstract description 25
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 24
- 229920000049 Carbon (fiber) Polymers 0.000 title abstract 4
- 239000004917 carbon fiber Substances 0.000 title abstract 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title abstract 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 87
- 239000000741 silica gel Substances 0.000 claims abstract description 87
- 229910002027 silica gel Inorganic materials 0.000 claims abstract description 87
- 238000000465 moulding Methods 0.000 claims abstract description 28
- 238000000034 method Methods 0.000 claims abstract description 18
- 238000012545 processing Methods 0.000 claims abstract description 15
- 238000005520 cutting process Methods 0.000 claims abstract description 9
- 239000002689 soil Substances 0.000 claims abstract description 8
- 230000008901 benefit Effects 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims abstract description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 24
- 229910052799 carbon Inorganic materials 0.000 claims description 24
- 238000013461 design Methods 0.000 claims description 23
- 239000000835 fiber Substances 0.000 claims description 21
- 238000005516 engineering process Methods 0.000 claims description 20
- 238000007493 shaping process Methods 0.000 claims description 17
- 239000004033 plastic Substances 0.000 claims description 15
- 239000007788 liquid Substances 0.000 claims description 9
- 239000002994 raw material Substances 0.000 claims description 7
- 239000000853 adhesive Substances 0.000 claims description 6
- 230000001070 adhesive effect Effects 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical group [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 238000004458 analytical method Methods 0.000 claims description 3
- 230000033228 biological regulation Effects 0.000 claims description 3
- 238000007598 dipping method Methods 0.000 claims description 3
- 238000000227 grinding Methods 0.000 claims description 3
- 239000004615 ingredient Substances 0.000 claims description 3
- 239000003755 preservative agent Substances 0.000 claims description 3
- 230000002335 preservative effect Effects 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 3
- 238000004901 spalling Methods 0.000 claims description 3
- 230000002269 spontaneous effect Effects 0.000 claims description 3
- 238000003756 stirring Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 claims description 3
- 239000004677 Nylon Substances 0.000 abstract description 6
- 229920001778 nylon Polymers 0.000 abstract description 6
- 238000000748 compression moulding Methods 0.000 abstract description 3
- 238000003754 machining Methods 0.000 abstract description 3
- 238000004026 adhesive bonding Methods 0.000 abstract 1
- 238000005266 casting Methods 0.000 abstract 1
- 239000011248 coating agent Substances 0.000 abstract 1
- 230000007547 defect Effects 0.000 abstract 1
- 238000009740 moulding (composite fabrication) Methods 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 abstract 1
- 238000009966 trimming Methods 0.000 abstract 1
- 238000010438 heat treatment Methods 0.000 description 5
- 230000008602 contraction Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012790 confirmation Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 235000012438 extruded product Nutrition 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
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Abstract
The invention discloses a production process of an aircraft made from a carbon fiber composite material with steps at the inner wall of a shell. The production process comprises the processing steps of confirming drawings, designing a silica gel inner container, designing and producing a mould, casting the silica gel inner container, preparing materials, cutting yarns, rolling the materials and forming, molding, trimming deflashing, cutting and processing, gluing, compensating soil and coating. The working procedures of designing and producing the silica gel inner container are increased on the basis of an existing compression molding process, the product is extruded by utilizing the expansion of the silica gel inner container after being heated to realize the molding of the aircraft made from the carbon fiber composite material with steps at the inner wall of the shell, after molding, and the silica gel inner container is taken out when the mould is cooled and the silica gel inner container is contracted after being cooled to obtain a finished product of the aircraft made from the carbon fiber composite material with steps at the inner wall of the shell. The production process disclosed by the invention can be used for overcoming the defects of the existing compression molding process and an air pressure molding process of a nylon air bag, and has the advantages of high production efficiency, high strength and good appearance of molded products, precise machining size and the like.
Description
Technical field
The invention belongs to carbon fibre composite aircraft field shaping technique, being specifically related to a kind of outer casing inner wall has the carbon fibre composite aircraft production technology of step.
Background technology
Conventional wall thickness is even, the wheel chair access carbon fibre composite aircraft of inwall generally can be by compression molding or nylon airbag air-pressure forming technological forming.die press technology for forming namely utilizes forming furnace table to mould pressurizing, heating, and by mould, give product pressurization to be formed, heating realizes the moulding of product, it comprises the drawing confirmation as shown in Figure 1, Design of Dies and manufacturing, get the raw materials ready, cut out yarn, the pre-type of coiled strip, moulding, the deburring processing of cutting, gummed, mend the procedure of processings such as soil and application, yet this die press technology for forming is not suitable for producing and does not wait wall thickness and product very light in weight, utilizing this die press technology for forming to produce outer casing inner wall has its Design of Dies of carbon fibre composite aircraft of step complicated, cost is high, even existence can't be produced above-mentioned outer casing inner wall the possibility of the carbon fibre composite aircraft of step.another moulding process is that nylon airbag air-pressure forming technology utilization forming furnace table is to mould pressurizing, heating, gases at high pressure enter the nylon airbag and from product cavity, product are exerted pressure by valve, forming furnace table heats mould simultaneously, realize formed product, its procedure of processing and die press technology for forming are basically identical, itself and die press technology for forming difference mainly increase and wear the airduct step in the pre-type of the coiled strip stage, be about to airduct and put in advance product cavity, yet above-mentioned nylon airbag air-pressure forming technique also can't be produced outer casing inner wall, the carbon fibre composite aircraft of step is arranged, its stepped form of carbon fibre composite aircraft that above-mentioned outer casing inner wall has a step for as shown in Figure 3 should glue together step by carry-on motor fixed head, comprise motor fixed head plate body 1 and step 10.
Can't produce outer casing inner wall with the technical problem of the carbon fibre composite aircraft of step as shown in Figure 3 for solving above-mentioned existing two kinds of moulding process, be badly in need of at present a solution and can realize that above-mentioned outer casing inner wall has the moulding production of the carbon fibre composite aircraft of step when guaranteeing shaped article intensity, machining accuracy and production efficiency.
Summary of the invention
For the deficiencies in the prior art, the present invention aims to provide the moulding production outer casing inner wall that is used for that a kind of production efficiency is high, machining accuracy accurate, shaped article intensity is good the technique of the carbon fibre composite aircraft of step.
For achieving the above object, the present invention adopts following technical scheme:
Outer casing inner wall has the carbon fibre composite aircraft production technology of step, comprise that drawing is confirmed, design silica gel inner container, Design of Dies and manufacturing, record silica gel inner container, get the raw materials ready, cut out yarn, coiled strip moulding, moulding, deburring processing of cutting, gummed, benefit soil and coating process step; The concrete technology step is as follows, step 1, and drawing is confirmed, according to product figure, carries out industrial analysis, whether assessment each position of product figure is fit to explained hereafter, as fillet, size etc., if there is improper explained hereafter position to revise product figure;
Step 3, Design of Dies and manufacturing, make respectively an aircraft shaping mould and a silica gel inner container making mould, this aircraft shaping mould is punching block, it is aluminum dipping form that silica gel inner container is made mould, and need to design the locked mode screw on above-mentioned aircraft shaping mould, the silica gel inner container bulbs of pressure are with aircraft spalling to be formed when avoiding mold cools down;
step 4, record silica gel inner container, silica gel inner container estimation silica gel inner container weight by the step 2 design, take in proportion two ingredient liquids silica gel, be placed in Plastic Drum, this Plastic Drum size is can just put vacuum tank into as good, stir, the Plastic Drum that liquid silica gel is housed is put into vacuum tank vacuumize 18-22 minute, pay close attention at any time silica gel situation in Plastic Drum, everywhere exit during Plastic Drum until silica gel, and pour the silica gel of liquid in step 3 silica gel inner container and make in the die cavity of mould, allow silica gel spontaneous curing 220-260 minute, after silica gel solidifies, silica gel inner container is made mould and taken out from silica gel inner container,
Step 5, get the raw materials ready, and, according to the regulation of aircraft product standard book, prepares moulding and produce required material;
Step 6, cut out yarn, and the structure chart that issues according to the engineer is cut into the carbon yarn specification that needs;
Step 7, the pre-type of coiled strip, record the silica gel inner container surface that obtains and wrap up the preservative film of the anti-180 ℃ of high temperature of one deck in step 4, and the structure chart that then according to engineer in step 6, issues rolls shape and the thickness of aircraft in advance, and tests;
Step 8, moulding, put into product rolled in step 7 the die cavity of aircraft shaping mould, and cover mold is also delivered to mould on the hot-platen stove plate of forming furnace table and is heated, and concrete tool parameters is set as oil pressure 100kg/cm
2, temperature 145-155 ℃, continue hot briquetting 15 minutes after product temperature reaches 150 ℃ in mould, then the aircraft shaping mould is delivered to cooling table cooling, and die sinking is also taken out the moulding aircraft;
Step 9, the deburring processing of cutting, with in type outer casing inner wall have step the deburring of carbon fibre composite aircraft, cut into needed size;
Step 11, mend soil, the aircraft surface in step 10 carried out grinding process, so that the aircraft outward appearance is clean and tidy;
Step 12, application, carry out baking vanish and the processing such as label by customer requirement to aircraft surface.
The present invention has following beneficial effect:
Outer casing inner wall of the present invention has the carbon fibre composite aircraft production technology of step, increase silica gel inner container and design and produce operation on existing die press technology for forming basis, utilize silica gel inner container expanded by heating extruded product to realize that outer casing inner wall has the moulding of the carbon fibre composite aircraft of step, treat mold cools down after moulding, the silica gel inner container contraction of catching a cold, take out silica gel inner container, obtain having the carbon fibre composite aircraft finished product that step is arranged as the outer casing inner wall of accompanying drawing 3 stepped form.Production technology of the present invention can overcome the deficiency of existing die press technology for forming and nylon airbag air-pressure forming technique, and has that production efficiency is high, shaped article intensity is high and the advantage such as good appearance, processing dimension be accurate.
Description of drawings
Fig. 1 is die press technology for forming flow chart of the prior art;
Fig. 2 is process chart of the present invention;
Fig. 3 is its motor glued board gummed step schematic diagram of carbon fibre composite aircraft that technique of the present invention outer casing inner wall to be processed has step;
Fig. 4 is its silica gel inner container structural representation of technique of the present invention.
The specific embodiment
Below in conjunction with drawings and the specific embodiments, the invention will be further described, so that clearerly understand the claimed technological thought of the present invention.
Outer casing inner wall of the present invention has the carbon fibre composite aircraft production technology of step, comprise as shown in Figure 2 that drawing is confirmed, design silica gel inner container, Design of Dies and manufacturing, record silica gel inner container, get the raw materials ready, cut out yarn, coiled strip moulding, moulding, deburring processing of cutting, gummed, benefit soil and coating process step, the concrete technology step is as follows:
step 4, record silica gel inner container 2, silica gel inner container 2 estimation silica gel inner container 2 weight by the step 2 design, take in proportion two ingredient liquids silica gel, be placed in Plastic Drum, this Plastic Drum size is can just put vacuum tank into as good, stir, the Plastic Drum that liquid silica gel is housed is put into vacuum tank vacuumize 18-22 minute, pay close attention at any time silica gel situation in Plastic Drum, everywhere exit during Plastic Drum until silica gel, and pour the silica gel of liquid in step 3 silica gel inner container and make in the die cavity of mould, allow silica gel spontaneous curing 220-260 minute, after silica gel solidifies, silica gel inner container 2 is made mould and taken out from silica gel inner container,
Step 5, get the raw materials ready, and, according to the regulation of aircraft product standard book, prepares moulding and produce required material;
Step 6, cut out yarn, and the structure chart that issues according to the engineer is cut into the carbon yarn specification that needs;
Step 7, the pre-type of coiled strip, record silica gel inner container 2 surfaces that obtain and wrap up the preservative film of the anti-180 ℃ of high temperature of one deck in step 4, and the structure chart that then according to engineer in step 6, issues rolls shape and the thickness of aircraft in advance, and tests;
Step 8, moulding, put into product rolled in step 7 the die cavity of aircraft shaping mould, and cover mold is also delivered to mould on the hot-platen stove plate of forming furnace table and is heated, and concrete tool parameters is set as oil pressure 100kg/cm
2, temperature 145-155 ℃, continue hot briquetting 15 minutes after product temperature reaches 150 ℃ in mould, then the aircraft shaping mould is delivered to cooling table cooling, and die sinking is also taken out the moulding aircraft;
Step 9, the deburring processing of cutting, with in type outer casing inner wall have step the deburring of carbon fibre composite aircraft, cut into needed size;
Step 11, mend soil, the aircraft surface in step 10 carried out grinding process, so that the aircraft outward appearance is clean and tidy;
Step 12, application, carry out baking vanish and the processing such as label by customer requirement to aircraft surface.
Technological principle of the present invention is: inside contract on the basis of product figure size before die sinking, design a silica gel inner container 2, open two sleeve forming moulds in the time of die sinking: a cover is the aircraft shaping mould, and a cover is that silica gel inner container is made mould; Utilize the pressure of silica gel inner container 2 expanded by heating that product is compressing during moulding, die sinking after mold cools down, the silica gel inner container 2 contraction size decreases of catching a cold, can take out very easily, thereby reach, produces the purpose of formal product as shown in Figure 3.
For a person skilled in the art, can make other various corresponding changes and distortion according to technical scheme described above and design, and these all changes and the distortion all should belong to the protection domain of the claims in the present invention within.
Claims (1)
1. outer casing inner wall has the carbon fibre composite aircraft production technology of step, it is characterized in that: comprise that drawing is confirmed, design silica gel inner container, Design of Dies and manufacturing, record silica gel inner container, get the raw materials ready, cut out yarn, coiled strip moulding, moulding, deburring processing of cutting, gummed, benefit soil and coating process step;
The concrete technology step is as follows, step 1, and drawing is confirmed, according to product figure, carries out industrial analysis, whether assessment each position of product figure is fit to explained hereafter, as fillet, size etc., if there is improper explained hereafter position to revise product figure;
Step 2, the design silica gel inner container, confirm after drawing monolateral inside contracting on the said goods figure overall dimensions basis, inside contract size depending on product thickness, silica gel inner container is monolateral particularly inside contracts 3 times that are of a size of aircraft wall thickness to be processed, determine silica gel inner container thickness after reserving silica gel inner container appearance and size, this silica gel inner container thickness requirement is even, and thickness is 3-5mm;
Step 3, Design of Dies and manufacturing, make respectively an aircraft shaping mould and a silica gel inner container making mould, this aircraft shaping mould is punching block, it is aluminum dipping form that silica gel inner container is made mould, and need to design the locked mode screw on above-mentioned aircraft shaping mould, the silica gel inner container bulbs of pressure are with aircraft spalling to be formed when avoiding mold cools down;
step 4, record silica gel inner container, silica gel inner container estimation silica gel inner container weight by the step 2 design, take in proportion two ingredient liquids silica gel, be placed in Plastic Drum, this Plastic Drum size is can just put vacuum tank into as good, stir, the Plastic Drum that liquid silica gel is housed is put into vacuum tank vacuumize 18-22 minute, pay close attention at any time silica gel situation in Plastic Drum, everywhere exit during Plastic Drum until silica gel, and pour the silica gel of liquid in step 3 silica gel inner container and make in the die cavity of mould, allow silica gel spontaneous curing 220-260 minute, after silica gel solidifies, silica gel inner container is made mould and taken out from silica gel inner container,
Step 5, get the raw materials ready, and, according to the regulation of aircraft product standard book, prepares moulding and produce required material;
Step 6, cut out yarn, and the structure chart that issues according to the engineer is cut into the carbon yarn specification that needs;
Step 7, the pre-type of coiled strip, record the silica gel inner container surface that obtains and wrap up the preservative film of the anti-180 ℃ of high temperature of one deck in step 4, and the structure chart that then according to engineer in step 6, issues rolls shape and the thickness of aircraft in advance, and tests;
Step 8, moulding, put into product rolled in step 7 the die cavity of aircraft shaping mould, and cover mold is also delivered to mould on the hot-platen stove plate of forming furnace table and is heated, and concrete tool parameters is set as oil pressure 100kg/cm
2, temperature 145-155 ℃, continue hot briquetting 15 minutes after product temperature reaches 150 ℃ in mould, then the aircraft shaping mould is delivered to cooling table cooling, and die sinking is also taken out the moulding aircraft;
Step 9, the deburring processing of cutting, with in type outer casing inner wall have step the deburring of carbon fibre composite aircraft, cut into needed size;
Step 10, the gummed, by adhesive with on aircraft, other can't be adhesive on aircraft body by integrated parts;
Step 11, mend soil, the aircraft surface in step 10 carried out grinding process, so that the aircraft outward appearance is clean and tidy;
Step 12, application, carry out baking vanish and the processing such as label by customer requirement to aircraft surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310302847.0A CN103395156B (en) | 2013-07-18 | 2013-07-18 | Outer casing inner wall has the carbon fibre composite aircraft production technology of step |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310302847.0A CN103395156B (en) | 2013-07-18 | 2013-07-18 | Outer casing inner wall has the carbon fibre composite aircraft production technology of step |
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| CN103395156A true CN103395156A (en) | 2013-11-20 |
| CN103395156B CN103395156B (en) | 2016-02-17 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105147463A (en) * | 2015-09-10 | 2015-12-16 | 上海迪诺克新材料科技有限公司 | Method for forming scoop stretcher |
| CN105773993A (en) * | 2016-05-19 | 2016-07-20 | 西华大学 | A carbon fiber tube for suspension of Formula Student racing car and its bonding process |
| CN106541586A (en) * | 2016-10-31 | 2017-03-29 | 河池学院 | A kind of preparation method of robotic weld arm |
| CN106994787A (en) * | 2017-06-02 | 2017-08-01 | 福建海源新材料科技有限公司 | The preparation facilities and method of a kind of carbon fibre composite of double-deck laminating |
| CN107031067A (en) * | 2017-05-10 | 2017-08-11 | 中国电子科技集团公司第二十六研究所 | A kind of preparation method of historical relic's protection carbon fiber capsule casket |
| CN109664521A (en) * | 2018-03-08 | 2019-04-23 | 中山市富达运动器材有限公司 | A kind of moulding process of carbon fibre composite Complex Parts |
| CN109719971A (en) * | 2017-10-27 | 2019-05-07 | 株洲电力机车广缘科技有限责任公司 | A kind of mold and its upper male mould manufacturing method for vacuum infusion molding |
| CN113043636A (en) * | 2019-12-28 | 2021-06-29 | 江苏亨睿碳纤维科技有限公司 | Manufacturing method of automobile carbon fiber composite material air filter box shell |
| CN113601765A (en) * | 2021-08-06 | 2021-11-05 | 厦门碳瀛复合材料科技有限公司 | High-appearance-demand carbon fiber product and compression molding method thereof |
| CN113895104A (en) * | 2021-10-18 | 2022-01-07 | 福建力仕机械有限公司 | Carbon fiber plate with soft covering layer and manufacturing method thereof |
| CN115489095A (en) * | 2022-09-28 | 2022-12-20 | 歌尔科技有限公司 | Carbon fiber composite material shell, preparation method thereof and electronic equipment |
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| CN101691065A (en) * | 2009-10-14 | 2010-04-07 | 上海理工大学 | Process for forming artificial leg made of carbon fiber composite materials |
| CN102320144A (en) * | 2011-06-30 | 2012-01-18 | 北京航空航天大学 | Manufacture die for carbon fiber composite integrative multipass joint and preparation method thereof |
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2013
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| JPS59144621A (en) * | 1983-01-28 | 1984-08-18 | Asahi Glass Co Ltd | Carbon fiber having improved elongation |
| US20060118992A1 (en) * | 2004-12-03 | 2006-06-08 | Geng-Wen Chang | Process of maniudacturing dual-layered thermal insulation composite panel |
| CN2776657Y (en) * | 2005-03-14 | 2006-05-03 | 胡宁 | Composite mould |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105147463A (en) * | 2015-09-10 | 2015-12-16 | 上海迪诺克新材料科技有限公司 | Method for forming scoop stretcher |
| CN105773993A (en) * | 2016-05-19 | 2016-07-20 | 西华大学 | A carbon fiber tube for suspension of Formula Student racing car and its bonding process |
| CN106541586A (en) * | 2016-10-31 | 2017-03-29 | 河池学院 | A kind of preparation method of robotic weld arm |
| CN107031067A (en) * | 2017-05-10 | 2017-08-11 | 中国电子科技集团公司第二十六研究所 | A kind of preparation method of historical relic's protection carbon fiber capsule casket |
| CN107031067B (en) * | 2017-05-10 | 2019-03-12 | 中国电子科技集团公司第二十六研究所 | A kind of production method of historical relic's protection carbon fiber capsule casket |
| CN106994787A (en) * | 2017-06-02 | 2017-08-01 | 福建海源新材料科技有限公司 | The preparation facilities and method of a kind of carbon fibre composite of double-deck laminating |
| CN109719971A (en) * | 2017-10-27 | 2019-05-07 | 株洲电力机车广缘科技有限责任公司 | A kind of mold and its upper male mould manufacturing method for vacuum infusion molding |
| CN109664521A (en) * | 2018-03-08 | 2019-04-23 | 中山市富达运动器材有限公司 | A kind of moulding process of carbon fibre composite Complex Parts |
| CN113043636A (en) * | 2019-12-28 | 2021-06-29 | 江苏亨睿碳纤维科技有限公司 | Manufacturing method of automobile carbon fiber composite material air filter box shell |
| CN113601765A (en) * | 2021-08-06 | 2021-11-05 | 厦门碳瀛复合材料科技有限公司 | High-appearance-demand carbon fiber product and compression molding method thereof |
| CN113895104A (en) * | 2021-10-18 | 2022-01-07 | 福建力仕机械有限公司 | Carbon fiber plate with soft covering layer and manufacturing method thereof |
| CN115489095A (en) * | 2022-09-28 | 2022-12-20 | 歌尔科技有限公司 | Carbon fiber composite material shell, preparation method thereof and electronic equipment |
| CN115489095B (en) * | 2022-09-28 | 2025-10-28 | 歌尔科技有限公司 | Carbon fiber composite material housing and preparation method thereof, and electronic equipment |
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| Publication number | Publication date |
|---|---|
| CN103395156B (en) | 2016-02-17 |
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