CN105525336A - Carbon fiber metal composite electronic product machine body structure and manufacturing method thereof - Google Patents
Carbon fiber metal composite electronic product machine body structure and manufacturing method thereof Download PDFInfo
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- CN105525336A CN105525336A CN201610053862.XA CN201610053862A CN105525336A CN 105525336 A CN105525336 A CN 105525336A CN 201610053862 A CN201610053862 A CN 201610053862A CN 105525336 A CN105525336 A CN 105525336A
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- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25F—PROCESSES FOR THE ELECTROLYTIC REMOVAL OF MATERIALS FROM OBJECTS; APPARATUS THEREFOR
- C25F3/00—Electrolytic etching or polishing
- C25F3/02—Etching
- C25F3/04—Etching of light metals
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04M—TELEPHONIC COMMUNICATION
- H04M1/00—Substation equipment, e.g. for use by subscribers
- H04M1/02—Constructional features of telephone sets
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- Chemical Or Physical Treatment Of Fibers (AREA)
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Abstract
The invention discloses a carbon fiber metal composite electronic product machine body structure. The carbon fiber metal composite electronic product machine body structure comprises an aluminum alloy frame and a carbon fiber middle frame plate which is located on the inner side of the aluminum alloy frame and integrally composited with the aluminum alloy frame. The aluminum alloy frame is provided with a micropore structure formed through surface corrosion treatment. The carbon fiber middle frame plate is combined with the surface of the aluminum alloy frame provided with the micropore structure to be integrally formed through hot-pressing solidification. The manufacturing method of the carbon fiber metal composite electronic product machine body structure comprises the steps that 1, the aluminum alloy frame is prepared; 2, surface corrosion treatment is conducted on the aluminum alloy frame, and thus the micropore structure is formed on the surface of the aluminum alloy frame; and 3, carbon fiber cloth is placed on the inner side of the aluminum alloy frame, 3 D molding and hot-pressing solidification treatment are conducted on the carbon fiber cloth, and after the carbon fiber cloth is treated, the carbon fiber cloth and the aluminum alloy frame are integrally combined to form the carbon fiber middle frame plate. The carbon fiber metal composite electronic product machine body structure is light in weight and high in strength and anti-pressure capacity.
Description
Technical field
The present invention relates to a kind of carbon fiber metal composite electron product airframe structure and preparation method thereof.
Background technology
At present along with the widespread use of carbon fibre material, carbon fiber is applied in electronic product by electron trade is at home a kind of trend.Carbon fibre material had both had the graceful firm characteristic of aluminum magnesium alloy, there is again the plasticity-of ABS engineering plastics, intensity and the capacity of heat transmission are better than again common ABS plastic, application on electronic product gets more and more, comprise the electronic product casing such as panel computer, phone housing, appearance and modeling requires also more and more rich and varied.
On mobile phone, applied metal material is the hot points and trends of mobile phone industry at present, because metallic substance can well promote the texture of mobile phone.High and the weight high characteristic of density due to metal, what the metallic substance of current choice for use was maximum is aluminium alloy, and material gently, is easily processed.And in view of aluminium metallic character, although lightweight, intensity is not high, greatly reduce the hardness of fuselage, occurred that fuselage anti-pressure ability is poor, be easy to problems such as being bent.Therefore, a kind of airframe structure that can meet high rigidity, excellent strength-weight ratio, the performance requriements such as anticorrosive, wear-resisting is urgently provided.
Summary of the invention
Main purpose of the present invention is to overcome the deficiencies in the prior art, a kind of carbon fiber metal composite electron product airframe structure and preparation method thereof is provided, the weight solving existing aluminium alloy fuselage is comparatively large but hardness is not high, and fuselage anti-pressure ability is poor, is easy to problems such as being bent.
For achieving the above object, the present invention is by the following technical solutions:
A kind of carbon fiber metal composite electron product airframe structure, comprise aluminum alloy frame and to be arranged in inside described aluminum alloy frame, with the carbon fiber deckle board of described aluminum alloy frame one volume recombination, described aluminum alloy frame has the microvoid structure formed through surface corrosion process, in described carbon fiber, deckle board combines with the surface with described microvoid structure of described aluminum alloy frame, is molded as one through hot-press solidifying.
Further:
The aperture of described micropore is 20 ~ 100 nanometers, and described micropore is evenly distributed on aluminum alloy frame surface.
In described carbon fiber, deckle board is the carbon fiber structural formed through 3D plastotype and hot-press solidifying process by the carbon cloth of staggered laying inside described aluminum alloy frame.
A making method for carbon fiber metal composite electron product airframe structure, comprises the following steps:
S1, preparation aluminum alloy frame;
S2, surface corrosion process is carried out to described aluminum alloy frame thus forms microvoid structure on the surface of described aluminum alloy frame;
S3, carbon cloth is placed on inside described aluminum alloy frame, 3D plastotype and hot-press solidifying process are carried out to described carbon cloth, form deckle board in the carbon fiber be combined as a whole with described aluminum alloy frame after process, wherein said aluminum alloy frame is hardened by the surface and described carbon fiber center with described microvoid structure and closes.
Further:
In step S2, described surface corrosion process comprises galvanic corrosion process.
The phosphoric acid mixed solution of the hydrochloric acid of described galvanic corrosion process employing 0.5 ~ 2mol/L, the sulfuric acid of 0.5 ~ 1.0mol/L, 0.5 ~ 1.0mol/L is as electrolytic solution.
Step S2 comprises: described aluminum alloy frame is put into the sodium hydroxide solution that mass concentration is 2% ~ 10%, heating in water bath 2 ~ 5 minutes, after cleaning, put into 1% ~ 10% salpeter solution, soak 3 ~ 10 minutes, again after cleaning, put in electrolyzer, the hydrochloric acid into 0.5 ~ 2mol/L is contained in groove, the sulfuric acid of 0.5 ~ 1.0mol/L, the phosphoric acid mixed solution of 0.5 ~ 1.0mol/L is as electrolytic solution, and add appropriate inhibiter, using described aluminum alloy frame as anode, in electrolyzer, graphite is as negative electrode, DC electrolysis 20 ~ 40s, current density controls at 0.10 ~ 0.30A/cm
2, tank liquor temperature controls at 30 ~ 50 DEG C, immerse acetone solution 5 ~ 10s after processing, afterwash and dry.
Step S3 comprises: carbon fibre initial rinse fabric is cut into predetermined size, then by the carbon cloth laying that cuts inside described aluminum alloy frame, for deckle board in the described carbon fiber of formation.
Step S3 also comprises: the carbon cloth that laying is good and described aluminum alloy frame put into 3D plastotype mould, and then plastotype 30 ~ 60s is transformed in heat pressing forming machines and carries out hot-press solidifying, solidification value is 135 ~ 150 DEG C, pressure 40 ~ 60kg, solidification 10 ~ 15min, then cools.
Also comprise after step S3: molding structure is carried out to the epoxy resin overflowed after carbon fibre initial rinse molding with cloth is removed in polishing.
Beneficial effect of the present invention:
The present invention adopts the airframe structure of deckle board composite molding in aluminum alloy frame and carbon fiber, solve existing aluminium alloy center hardness not high, the problems such as anti-pressure ability is poor and be easily bent, also reduce the weight of aluminium alloy fuselage, and can not destroy the metal-like of mobile phone complete machine.Be integrated to make aluminum alloy frame and carbon fiber center sheet metal forming, in the present invention, aluminum alloy frame has the microvoid structure formed through surface corrosion process, aluminum alloy frame has deckle board in the surface of microvoid structure and carbon fiber by it and forms bonding interface, be molded as one through hot-press solidifying, microvoid structure on aluminum alloy frame effectively strengthens the bonding force between both interfaces, improves the adhesion strength that carbon fiber is combined with aluminium alloy.Carbon-fibre composite quality is light, intensity large, and weight is only equivalent to 20% to 30% of steel, and hardness is but more than 10 times of steel.Carbon fiber metal composite airframe structural provided by the invention takes full advantage of carbon-fibre composite lightweight, high-strength, Gao Mo, resistance to chemical attack, the characteristics such as thermal expansivity is little, relative to existing aluminium alloy center, the invention enables whole fuselage middle frame structure intensity to strengthen 1/3, quality can reduce 1/3.
Accompanying drawing explanation
Fig. 1 is the aluminum alloy frame structural representation in an embodiment of the present invention;
Fig. 2 is the carbon fiber metal composite airframe structural schematic diagram of an embodiment of the present invention.
Embodiment
Below embodiments of the present invention are elaborated.It is emphasized that following explanation is only exemplary, instead of in order to limit the scope of the invention and apply.
Consult Fig. 1 and Fig. 2, in one embodiment, a kind of carbon fiber metal composite electron product airframe structure, comprise aluminum alloy frame 1 and to be arranged in inside described aluminum alloy frame 1, with the carbon fiber deckle board 2 of described aluminum alloy frame 1 one volume recombination, described aluminum alloy frame 1 has the microvoid structure (not shown) formed through surface corrosion process, in described carbon fiber, deckle board 2 combines with the surface with described microvoid structure of described aluminum alloy frame 1, is molded as one through hot-press solidifying.
In a preferred embodiment, the aperture of the micropore on aluminum alloy frame 1 is 20 ~ 100 nanometers, and described micropore is evenly distributed on the surface of aluminum alloy frame 1.
In a preferred embodiment, in described carbon fiber, deckle board 2 is the carbon fiber structurals formed through 3D plastotype and hot-press solidifying process by the carbon cloth of staggered laying inside described aluminum alloy frame 1.
In a kind of preferred embodiment, in carbon fiber, the thickness of deckle board 2 is 0.5mm.
Consult Fig. 1 and Fig. 2, in one embodiment, a kind of making method of carbon fiber metal composite electron product airframe structure, comprises the following steps:
S1, preparation aluminum alloy frame 1;
S2, surface corrosion process is carried out to described aluminum alloy frame 1 thus forms microvoid structure on the surface of described aluminum alloy frame 1;
S3, carbon cloth is placed on inside described aluminum alloy frame 1,3D plastotype and hot-press solidifying process are carried out to described carbon cloth, form deckle board 2 in the carbon fiber be combined as a whole with described aluminum alloy frame 1 after process, wherein said aluminum alloy frame 1 is combined by surface deckle board 2 in described carbon fiber with described microvoid structure.
In a preferred embodiment, in step S2, described surface corrosion process comprises galvanic corrosion process.In a more preferred embodiment, described galvanic corrosion process adopts the phosphoric acid mixed solution of the sulfuric acid of the hydrochloric acid of 0.5 ~ 2mol/L, 0.5 ~ 1.0mol/L, 0.5 ~ 1.0mol/L as electrolytic solution.
In a more preferred embodiment, step S2 comprises: described aluminum alloy frame 1 is put into the sodium hydroxide solution that mass concentration is 2% ~ 10%, heating in water bath 2 ~ 5 minutes, after cleaning, put into 1% ~ 10% salpeter solution, soak 3 ~ 10 minutes, again after cleaning, put in electrolyzer, the hydrochloric acid into 0.5 ~ 2mol/L is contained in groove, the sulfuric acid of 0.5 ~ 1.0mol/L, the phosphoric acid mixed solution of 0.5 ~ 1.0mol/L is as electrolytic solution, and add appropriate inhibiter, using described aluminum alloy frame 1 as anode, in electrolyzer, graphite is as negative electrode, DC electrolysis 20 ~ 40s, current density controls at 0.10 ~ 0.30A/cm
2, tank liquor temperature controls at 30 ~ 50 DEG C, immerse acetone solution 5 ~ 10s after processing, afterwash and dry.
In a preferred embodiment, step S3 comprises: carbon fibre initial rinse fabric is cut into predetermined size, then by the carbon cloth laying that cuts inside described aluminum alloy frame 1, for deckle board 2 in the described carbon fiber of formation.
In a preferred embodiment, step S3 also comprises: the carbon cloth that laying is good and described aluminum alloy frame 1 put into 3D plastotype mould, plastotype 30 ~ 60s, then be transformed in heat pressing forming machines and carry out hot-press solidifying, solidification value is 135 ~ 150 DEG C, pressure 40 ~ 60kg, solidification 10 ~ 15min, then cool, obtain aluminum alloy frame 1 and the integrated composite structure of deckle board 2 in carbon fiber.
In a preferred embodiment, also comprise after step S3: molding structure is carried out to the epoxy resin overflowed after carbon fibre initial rinse molding with cloth is removed in polishing.
In a particular embodiment, time prepared by aluminum alloy frame 1, first by the aluminium sheet of extruded aluminium stockline cutting fixed measure, CNC machine milling inner cavities can be re-used, then through precision work process, obtains aluminum alloy frame product.When aluminum alloy frame 1 carries out micropore process, aluminum alloy frame 1 product first can be placed in scavenging solution to process, chemical surface treatment is carried out again in acid solution and alkali lye, then be placed in chemical corrosion liquid and carry out micropore process, thus obtain the aluminum alloy frame 1 with certain microvoid structure, the aperture of micropore is 20 ~ 100 nanometers, is evenly distributed on aluminum alloy frame 1 surface.Deckle board 2 one compound tense in aluminum alloy frame 1 with carbon fiber, the aluminum alloy frame 1 with microvoid structure can be placed in 3D plastotype mould, ready carbon cloth is interlocked in the middle of laying and aluminum alloy frame, then 3D plastotype is carried out, then putting into hot-press solidifying again, to carry out hot-press solidifying shaping, after taking-up, carry out corresponding surface treatment and namely obtain aluminium alloy carbon fiber compound center product.
Aluminum alloy frame 1 and carbon fiber are combined into an overall center, carbon-fibre composite is utilized to have light and strong, light and firm, corrosion-resistant, antifatigue, scantlings of the structure good stability, the hardness of center can not only be increased, improve the anti-pressure ability of middle frame structure, also reduce the weight of center, and overall performance and the metal-like effect of center can not be affected, its quality compares all aluminium alloy center can alleviate 10%, intensity can increase by 30%, anti-pressure ability can increase by 20%, and the crushing resistance of middle deckle board 2 can play self-regeneration effect for nondestructive pressure.
Example
The preparation of aluminum alloy frame
Aluminum or aluminum alloy aluminium extruded is fixed on fixture, cuts out the aluminium alloy plate of 160mm*80mm*10mm with Linear cut, then this aluminium alloy plate is loaded in CNC board and rough mill inner chamber and locating dowel, then fix frame with fixture, precision work inner-cavity structure.Taking-up greasy dirt cleaning machine cleaning aluminum alloy frame after processing, wipe oil, then clean by washed with de-ionized water, dry in an oven.
The process of aluminum alloy frame micropore
First above-mentioned aluminum alloy frame is put into 2% ~ 10% sodium hydroxide solution, 40 DEG C of heating in water bath are in 2 ~ 5 minutes, then clean by washed with de-ionized water; Then will put into 1% ~ 10% salpeter solution, soak 3 ~ 10 minutes, same washed with de-ionized water after having soaked; Then frame is put in electrolyzer, phosphoric acid mixed solution into the sulfuric acid of the hydrochloric acid of 0.5 ~ 2mol/L, 0.5 ~ 1.0mol/L, 0.5 ~ 1.0mol/L is contained as electrolytic solution in groove, and add certain inhibiter, using frame as anode, in electrolyzer, graphite is as negative electrode, DC electrolysis 20 ~ 40s, current density controls at 0.10 ~ 0.30A/cm
2, tank liquor temperature controls at 40 DEG C; Then take out and immerse acetone 5 ~ 10s, then clean with deionized water and dry.
Aluminum alloy frame and carbon fibre integrated compound
The frame of micropore process is encased in 3D plastotype mould, location is fixing, then by carbon fibre initial rinse fabric cut into 140mm*80mm, again by the carbon cloth that cuts according to demand laying in scuncheon, and put into 3D plastotype mould and carry out inner-cavity structure plastotype, plastotype 30 ~ 60s, then hot-press solidifying in heat pressing forming machines is transformed into, solidification value is 135 ~ 150 DEG C, pressure 40 ~ 60kg, solidification 10 ~ 15min, cooling die is to room temperature, the product taken out inside mould just obtains integral product, and then carry out the epoxy resin that shaping spilling is removed in the meticulous polishing of inner frame structure, aluminum alloy frame and carbon fibre integrated composite rim can be obtained.
Through actual measurement, the carbon fiber metal composite airframe structural weight obtained by above-mentioned example is 63g, compared with specification of the same race but the overall airframe structure weight (70g) of aluminium alloy center that adopts approximately alleviates 7g, wherein in carbon fiber, the ultimate compression strength (6.5MP power) of the compressive strength rate aluminium alloy center of deckle board increases 2MP.
Above content combines concrete/preferred embodiment further description made for the present invention, can not assert that specific embodiment of the invention is confined to these explanations.For general technical staff of the technical field of the invention; without departing from the inventive concept of the premise; its embodiment that can also describe these makes some substituting or modification, and these substitute or variant all should be considered as belonging to protection scope of the present invention.
Claims (10)
1. a carbon fiber metal composite electron product airframe structure, it is characterized in that, comprise aluminum alloy frame and to be arranged in inside described aluminum alloy frame, with the carbon fiber deckle board of described aluminum alloy frame one volume recombination, described aluminum alloy frame has the microvoid structure formed through surface corrosion process, in described carbon fiber, deckle board combines with the surface with described microvoid structure of described aluminum alloy frame, is molded as one through hot-press solidifying.
2. carbon fiber metal composite electron product airframe structure as claimed in claim 1, it is characterized in that, the aperture of described micropore is 20 ~ 100 nanometers, and described micropore is evenly distributed on aluminum alloy frame surface.
3. carbon fiber metal composite electron product airframe structure as claimed in claim 1 or 2, it is characterized in that, in described carbon fiber, deckle board is the carbon fiber structural formed through 3D plastotype and hot-press solidifying process by the carbon cloth of staggered laying inside described aluminum alloy frame.
4. a making method for carbon fiber metal composite electron product airframe structure, is characterized in that, comprise the following steps:
S1, preparation aluminum alloy frame;
S2, surface corrosion process is carried out to described aluminum alloy frame thus forms microvoid structure on the surface of described aluminum alloy frame;
S3, carbon cloth is placed on inside described aluminum alloy frame, 3D plastotype and hot-press solidifying process are carried out to described carbon cloth, form deckle board in the carbon fiber be combined as a whole with described aluminum alloy frame after process, wherein said aluminum alloy frame is hardened by the surface and described carbon fiber center with described microvoid structure and closes.
5. the making method of carbon fiber metal composite electron product airframe structure as claimed in claim 4, it is characterized in that, in step S2, described surface corrosion process comprises galvanic corrosion process.
6. the making method of carbon fiber metal composite electron product airframe structure as claimed in claim 5, it is characterized in that, the phosphoric acid mixed solution of the hydrochloric acid of described galvanic corrosion process employing 0.5 ~ 2mol/L, the sulfuric acid of 0.5 ~ 1.0mol/L, 0.5 ~ 1.0mol/L is as electrolytic solution.
7. the making method of carbon fiber metal composite electron product airframe structure as claimed in claim 6, it is characterized in that, step S2 comprises: described aluminum alloy frame is put into the sodium hydroxide solution that mass concentration is 2% ~ 10%, heating in water bath 2 ~ 5 minutes, after cleaning, put into 1% ~ 10% salpeter solution, soak 3 ~ 10 minutes, again after cleaning, put in electrolyzer, the hydrochloric acid into 0.5 ~ 2mol/L is contained in groove, the sulfuric acid of 0.5 ~ 1.0mol/L, the phosphoric acid mixed solution of 0.5 ~ 1.0mol/L is as electrolytic solution, and add appropriate inhibiter, using described aluminum alloy frame as anode, in electrolyzer, graphite is as negative electrode, DC electrolysis 20 ~ 40s, current density controls at 0.10 ~ 0.30A/cm
2, tank liquor temperature controls at 30 ~ 50 DEG C, immerse acetone solution 5 ~ 10s after processing, afterwash and dry.
8. the making method of the carbon fiber metal composite electron product airframe structure as described in any one of claim 4 to 7, it is characterized in that, step S3 comprises: carbon fibre initial rinse fabric is cut into predetermined size, again by the carbon cloth laying that cuts inside described aluminum alloy frame, for deckle board in the described carbon fiber of formation.
9. the making method of carbon fiber metal composite electron product airframe structure as claimed in claim 8, it is characterized in that, step S3 also comprises: the carbon cloth that laying is good and described aluminum alloy frame put into 3D plastotype mould, plastotype 30 ~ 60s, then be transformed in heat pressing forming machines and carry out hot-press solidifying, solidification value is 135 ~ 150 DEG C, pressure 40 ~ 60kg, solidification 10 ~ 15min, then cools.
10. the making method of the carbon fiber metal composite electron product airframe structure as described in any one of claim 4 to 9, is characterized in that, also comprise after step S3: molding structure is carried out to the epoxy resin overflowed after carbon fibre initial rinse molding with cloth is removed in polishing.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105827759A (en) * | 2016-05-06 | 2016-08-03 | 东莞劲胜精密组件股份有限公司 | Electronic product frame structure made of carbon fiber ceramic composite material and manufacturing method of the structure |
| CN106025521A (en) * | 2016-07-13 | 2016-10-12 | 东莞劲胜精密组件股份有限公司 | Carbon fiber composite material antenna and preparation method thereof |
| CN106131255A (en) * | 2016-08-16 | 2016-11-16 | 东莞劲胜精密组件股份有限公司 | A kind of rustless steel carbon fibre composite mobile phone framework and preparation method thereof |
| CN106363869A (en) * | 2016-10-25 | 2017-02-01 | 深圳市宝元金实业有限公司 | Method for forming nano-voids in surface of metal substrate |
| CN107613048A (en) * | 2017-08-29 | 2018-01-19 | 广东长盈精密技术有限公司 | Mobile phone center and its manufacture method |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202551553U (en) * | 2012-04-05 | 2012-11-21 | 东莞劲胜精密组件股份有限公司 | Novel electronic product structural part |
| CN103276435A (en) * | 2013-05-21 | 2013-09-04 | 东莞劲胜精密组件股份有限公司 | Micro-nano processing method for aluminum/aluminum alloy surface and aluminum/ aluminum alloy structure |
| CN103297565A (en) * | 2012-02-24 | 2013-09-11 | 比亚迪股份有限公司 | Mobile phone shell and preparation method thereof |
| CN103841784A (en) * | 2014-03-18 | 2014-06-04 | 亚超特工业有限公司 | Forming method of internal middle frame board of electronic device and internal middle frame board |
| CN104411126A (en) * | 2014-11-14 | 2015-03-11 | 东莞劲胜精密组件股份有限公司 | Electronic product housing and manufacturing method thereof |
| CN105128260A (en) * | 2015-09-30 | 2015-12-09 | 东莞市中泰模具股份有限公司塘厦分公司 | Metal shell of electronic product and manufacturing method of metal shell |
| CN205529133U (en) * | 2016-01-26 | 2016-08-31 | 东莞劲胜精密组件股份有限公司 | Carbon fiber metal composite electron product fuselage structure |
-
2016
- 2016-01-26 CN CN201610053862.XA patent/CN105525336B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103297565A (en) * | 2012-02-24 | 2013-09-11 | 比亚迪股份有限公司 | Mobile phone shell and preparation method thereof |
| CN202551553U (en) * | 2012-04-05 | 2012-11-21 | 东莞劲胜精密组件股份有限公司 | Novel electronic product structural part |
| CN103276435A (en) * | 2013-05-21 | 2013-09-04 | 东莞劲胜精密组件股份有限公司 | Micro-nano processing method for aluminum/aluminum alloy surface and aluminum/ aluminum alloy structure |
| CN103841784A (en) * | 2014-03-18 | 2014-06-04 | 亚超特工业有限公司 | Forming method of internal middle frame board of electronic device and internal middle frame board |
| CN104411126A (en) * | 2014-11-14 | 2015-03-11 | 东莞劲胜精密组件股份有限公司 | Electronic product housing and manufacturing method thereof |
| CN105128260A (en) * | 2015-09-30 | 2015-12-09 | 东莞市中泰模具股份有限公司塘厦分公司 | Metal shell of electronic product and manufacturing method of metal shell |
| CN205529133U (en) * | 2016-01-26 | 2016-08-31 | 东莞劲胜精密组件股份有限公司 | Carbon fiber metal composite electron product fuselage structure |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105827759A (en) * | 2016-05-06 | 2016-08-03 | 东莞劲胜精密组件股份有限公司 | Electronic product frame structure made of carbon fiber ceramic composite material and manufacturing method of the structure |
| CN106025521A (en) * | 2016-07-13 | 2016-10-12 | 东莞劲胜精密组件股份有限公司 | Carbon fiber composite material antenna and preparation method thereof |
| CN106025521B (en) * | 2016-07-13 | 2019-06-04 | 广东劲胜智能集团股份有限公司 | A kind of carbon fibre composite antenna and preparation method thereof |
| CN106131255A (en) * | 2016-08-16 | 2016-11-16 | 东莞劲胜精密组件股份有限公司 | A kind of rustless steel carbon fibre composite mobile phone framework and preparation method thereof |
| CN109309739A (en) * | 2016-09-18 | 2019-02-05 | 广东劲胜智能集团股份有限公司 | Titanium alloy plastic composite mobile phone frame stand manufacturing method based on microporous processing |
| CN106363869A (en) * | 2016-10-25 | 2017-02-01 | 深圳市宝元金实业有限公司 | Method for forming nano-voids in surface of metal substrate |
| CN107613048A (en) * | 2017-08-29 | 2018-01-19 | 广东长盈精密技术有限公司 | Mobile phone center and its manufacture method |
| CN113334804A (en) * | 2021-06-30 | 2021-09-03 | 成都飞机工业（集团）有限责任公司 | Fiber-reinforced metal laminate liquid medium curing and forming process |
| CN114474793A (en) * | 2021-12-31 | 2022-05-13 | 歌尔股份有限公司 | Carbon fiber metal composite material and preparation method thereof |
| CN117651087A (en) * | 2024-01-30 | 2024-03-05 | 东莞市维斯德新材料技术有限公司 | Carbon fiber mobile phone middle frame and preparation method thereof |
| CN117651087B (en) * | 2024-01-30 | 2024-04-16 | 东莞市维斯德新材料技术有限公司 | Carbon fiber mobile phone middle frame and preparation method thereof |
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