CN105525336B - A kind of carbon fiber metal composite electron product airframe structure and preparation method thereof - Google Patents
A kind of carbon fiber metal composite electron product airframe structure and preparation method thereof Download PDFInfo
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- CN105525336B CN105525336B CN201610053862.XA CN201610053862A CN105525336B CN 105525336 B CN105525336 B CN 105525336B CN 201610053862 A CN201610053862 A CN 201610053862A CN 105525336 B CN105525336 B CN 105525336B
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- aluminum alloy
- alloy frame
- carbon fiber
- metal composite
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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
-
- 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
Abstract
The invention discloses a kind of carbon fiber metal composite electron product airframe structure, including aluminum alloy frame and deckle board on the inside of aluminum alloy frame and in the carbon fiber of the bluk recombination of aluminum alloy frame one, aluminum alloy frame has the microcellular structure formed through surface corrosion processing, deckle board is combined with the surface with microcellular structure of aluminum alloy frame in carbon fiber, is molded as one through hot-press solidifying.A kind of preparation method of carbon fiber metal composite electron product airframe structure, including：Prepare aluminum alloy frame；Surface corrosion processing is carried out to aluminum alloy frame so as to form microcellular structure on the surface of aluminum alloy frame；Carbon cloth is placed on the inside of aluminum alloy frame, 3D plastotypes are carried out to carbon cloth and hot-press solidifying is handled, deckle board in the carbon fiber being combined as a whole with aluminum alloy frame is formed after processing.The carbon fiber metal composite electron product airframe structure lighter in weight, intensity is high, and anti-pressure ability is strong.
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
Now with the extensive use of carbon fibre material, carbon fiber is applied in electronic product by electronics industry at home is
A kind of trend.Carbon fibre material had both possessed the graceful firm characteristic of almag, there is the plasticity of ABS engineering plastics, intensity again
It is better than common ABS plastic again with the capacity of heat transmission, the application on electronic product is more and more, including outside tablet personal computer, mobile phone
The electronic product casings such as shell, appearance and modeling require also more and more rich and varied.
Applied metal material is the focus and trend of mobile phone industry on mobile phone at present, because metal material can be very good
Lift the texture of mobile phone.Because the density of metal is high and the high characteristic of weight, the metal material for selecting to use at present at most be aluminium
Alloy, material is light, easy processing.And in view of aluminium metallic character, although lightweight, intensity is not high, greatly reduce fuselage
Hardness, it is poor to there is fuselage anti-pressure ability, it is easy to the problems such as being bent.It would therefore be highly desirable to high rigidity, excellent can be met by providing one kind
The airframe structure of the performance requirement such as different strength-weight ratio, anticorrosive, wear-resisting.
The content of the invention
It is a primary object of the present invention to overcome the deficiencies in the prior art, there is provided a kind of carbon fiber metal composite electron product
Airframe structure and preparation method thereof, solves that the weight of existing aluminium alloy fuselage is larger but hardness is not high, and fuselage anti-pressure ability is poor, very
The problems such as being easily bent.
To achieve the above object, the present invention uses following technical scheme：
A kind of carbon fiber metal composite electron product airframe structure, including aluminum alloy frame is with being located at the aluminum alloy frame
Deckle board in the carbon fiber of inner side and the bluk recombination of aluminum alloy frame one, the aluminum alloy frame has to be handled through surface corrosion
The microcellular structure of formation, the surface with the microcellular structure of deckle board and the aluminum alloy frame is mutually tied in the carbon fiber
Close, be molded as one through hot-press solidifying.
Further：
The aperture of the micropore is 20~100 nanometers, and the micropore is evenly distributed on aluminum alloy frame surface.
In the carbon fiber deckle board be by carbon cloth of the laying on the inside of the aluminum alloy frame that interlock through 3D plastotypes and
The carbon fiber structural that hot-press solidifying is handled and formed.
A kind of preparation method of carbon fiber metal composite electron product airframe structure, comprises the following steps：
S1, prepare aluminum alloy frame；
S2, surface corrosion processing is carried out to the aluminum alloy frame so as to form micropore on the surface of the aluminum alloy frame
Structure；
S3, carbon cloth is placed on the inside of the aluminum alloy frame, 3D plastotypes and hot pressing are carried out to the carbon cloth
Curing process, deckle board in the carbon fiber being combined as a whole with the aluminum alloy frame is formed after processing, wherein the aluminium alloy side
Frame passes through the surface with the microcellular structure and the hardened conjunction of carbon fiber center.
Further：
In step S2, the surface corrosion processing includes electrochemical corrosion processing.
Electrochemical corrosion processing using 0.5~2mol/L hydrochloric acid, 0.5~1.0mol/L sulfuric acid, 0.5~
1.0mol/L phosphoric acid mixed liquor is as electrolyte.
Step S2 includes：The aluminum alloy frame is put into the sodium hydroxide solution that mass concentration is 2%~10%, water
Bath heating 2~5 minutes, after cleaning, is put into 1%~10% salpeter solution, soaks 3~10 minutes, after cleaning again, is put into
The hydrochloric acid into 0.5~2mol/L, 0.5~1.0mol/L sulfuric acid, 0.5~1.0mol/L phosphoric acid is contained in electrolytic cell, in groove to mix
Liquid is closed as electrolyte, and adds appropriate corrosion inhibiter, using the aluminum alloy frame as anode, is made with graphite in electrolytic cell
For negative electrode, 20~40s of DC electrolysis, current density is controlled in 0.10~0.30A/cm2, tank liquor temperature control is at 30~50 DEG C；
5~10s of acetone solution is immersed after having handled, cleans and dries afterwards.
Step S3 includes：Carbon fibre initial rinse fabric is cut into preliminary dimension, then by the carbon cloth laying cut in institute
State on the inside of aluminum alloy frame, for forming deckle board in the carbon fiber.
Step S3 also includes：The good carbon cloth of laying and the aluminum alloy frame are put into 3D plastotype moulds, plastotype
30~60s, then switching to and hot-press solidifying is carried out in heat pressing forming machines, solidification temperature is 135~150 DEG C, 40~60kg of pressure,
Solidify 10~15min, then cool down.
Also include after step S3：Polishing is carried out to molding structure and removes the asphalt mixtures modified by epoxy resin overflowed after carbon fibre initial rinse molding with cloth
Fat.
Beneficial effects of the present invention：
The present invention is solved existing aluminium and closed using the airframe structure of deckle board composite molding in aluminum alloy frame and carbon fiber
Golden center hardness is not high, anti-pressure ability difference and easy the problems such as being bent, and also reduces the weight of aluminium alloy fuselage, and will not
Destroy the metal-like of mobile phone complete machine.In order that aluminum alloy frame and carbon fiber center sheet metal forming are integrated, aluminium closes in the present invention
Golden-rimmed frame has the microcellular structure formed through surface corrosion processing, and aluminum alloy frame has surface and the carbon of microcellular structure by it
Fiber center plate shape is molded as one, the effectively enhancing two of the microcellular structure on aluminum alloy frame into combination interface through hot-press solidifying
Adhesion between person interface, improve the adhesive strength that carbon fiber is combined with aluminium alloy.Carbon fibre composite light weight, intensity
Greatly, weight just corresponds to 20% to the 30% of steel, and hardness is more than 10 times of steel.Carbon fiber metal provided by the invention
Composite airframe structural takes full advantage of carbon fibre composite lightweight, and high-strength, Gao Mo is resistant to chemical etching, and thermal coefficient of expansion is small etc.
Characteristic, relative to existing aluminium alloy center, the invention enables whole fuselage middle frame structure intensity can strengthen 1/3, and quality can subtract
Few 1/3.
Brief description of the drawings
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
Embodiments of the present invention are elaborated below.It is emphasized that what the description below was merely exemplary,
The scope being not intended to be limiting of the invention and its application.
Refering to Fig. 1 and Fig. 2, in one embodiment, a kind of carbon fiber metal composite electron product airframe structure, including aluminium
Alloy frame 1 and the deckle board 2 in the inner side of aluminum alloy frame 1, the carbon fiber with the bluk recombination of aluminum alloy frame 1 one,
The aluminum alloy frame 1 has the microcellular structure (not shown) formed through surface corrosion processing, deckle board 2 and institute in the carbon fiber
The surface with the microcellular structure for stating aluminum alloy frame 1 is combined, and 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 the micropore is uniform
It is distributed in the surface of aluminum alloy frame 1.
In a preferred embodiment, deckle board 2 is in the inner side of aluminum alloy frame 1 by the laying that interlocks in the carbon fiber
The carbon fiber structural that carbon cloth is handled and formed through 3D plastotypes and hot-press solidifying.
In a kind of preferred embodiment, the thickness of deckle board 2 is 0.5mm in carbon fiber.
Refering to Fig. 1 and Fig. 2, in one embodiment, a kind of making of carbon fiber metal composite electron product airframe structure
Method, comprise the following steps：
S1, prepare aluminum alloy frame 1；
S2, surface corrosion processing is carried out to the aluminum alloy frame 1 so as to be formed on the surface of the aluminum alloy frame 1 micro-
Pore structure；
S3, carbon cloth is placed on to the inner side of the aluminum alloy frame 1,3D plastotypes and hot pressing are carried out to the carbon cloth
Curing process, deckle board 2 in the carbon fiber being combined as a whole with the aluminum alloy frame 1 is formed after processing, wherein the aluminium alloy
Frame 1 is combined by the surface with the microcellular structure with deckle board 2 in the carbon fiber.
In a preferred embodiment, in step S2, the surface corrosion processing includes electrochemical corrosion processing.More preferably
Embodiment in, electrochemical corrosion processing using 0.5~2mol/L hydrochloric acid, 0.5~1.0mol/L sulfuric acid, 0.5~
1.0mol/L phosphoric acid mixed liquor is as electrolyte.
In a more preferred embodiment, step S2 includes：By the aluminum alloy frame 1 be put into mass concentration for 2%~
In 10% sodium hydroxide solution, heating water bath 2~5 minutes, after cleaning, it is put into 1%~10% salpeter solution, immersion 3~
10 minutes, after cleaning again, it is put into electrolytic cell, hydrochloric acid, the 0.5~1.0mol/L sulphur into 0.5~2mol/L is contained in groove
Acid, 0.5~1.0mol/L phosphoric acid mixed liquor add appropriate corrosion inhibiter as electrolyte, with the aluminum alloy frame 1
As anode, graphite is controlled in 0.10~0.30A/ as negative electrode, 20~40s of DC electrolysis, current density using in electrolytic cell
cm2, tank liquor temperature control is at 30~50 DEG C；5~10s of acetone solution is immersed after having handled, cleans and dries afterwards.
In a preferred embodiment, step S3 includes：Carbon fibre initial rinse fabric cut into preliminary dimension, then will have been cut
Carbon cloth laying is in the inner side of aluminum alloy frame 1, for forming deckle board 2 in the carbon fiber.
In a preferred embodiment, step S3 also includes：The good carbon cloth of laying and the aluminum alloy frame 1 are put into
In 3D plastotype moulds, 30~60s of plastotype, then switch to and hot-press solidifying carried out in heat pressing forming machines, solidification temperature be 135~
150 DEG C, 40~60kg of pressure, solidify 10~15min, then cool down, obtain aluminum alloy frame 1 and the one of deckle board in carbon fiber 2
The composite construction of shaping.
In a preferred embodiment, also include after step S3：Polishing is carried out to molding structure and removes carbon fibre initial rinse fabric
The epoxy resin overflowed after shaping.
In a particular embodiment, when prepared by aluminum alloy frame 1, aluminium extruded line of material can first be cut to the aluminium sheet of fixed dimension,
CNC machine milling inner cavities are reused, are then handled by finishing, obtain aluminum alloy frame product.It is enterprising in aluminum alloy frame 1
During the processing of row micropore, the product of aluminum alloy frame 1 can be first placed in cleaning fluid and handled, then by carrying out chemistry in acid solution and alkali lye
Surface treatment, progress micropore processing in chemical corrosion liquid is subsequently placed in, so as to obtain the aluminium alloy side with certain microcellular structure
Frame 1, the aperture of micropore is 20~100 nanometers, is evenly distributed on the surface of aluminum alloy frame 1.In aluminum alloy frame 1 and carbon fiber
2 integral compound tense of deckle board, the aluminum alloy frame 1 with microcellular structure can be placed in 3D plastotype moulds, ready carbon is fine
Wei Bu interlocks among laying and aluminum alloy frame, then carries out 3D plastotypes, then places into and hot-press solidifying is carried out in hot-press solidifying
Shaping, after taking-up, carry out corresponding surface treatment and obtain the compound center product of aluminium alloy carbon fiber.
Aluminum alloy frame 1 and carbon fiber are combined into the center of an entirety, using carbon fibre composite have it is light and
By force, light and firm, corrosion-resistant, endurance, physical dimension stability are good, can not only increase the hardness of center, improve middle frame structure
Anti-pressure ability, also reduces the weight of center, and does not interfere with the overall performance and metal-like effect of center, and its quality is compared
All aluminium alloy center can mitigate 10%, and intensity can increase by 30%, and anti-pressure ability can increase by 20%, and the crushing resistance of middle deckle board 2
It can play self-regeneration for nondestructive pressure.
Example
The preparation of aluminum alloy frame
Aluminum or aluminum alloy aluminium extruded is fixed on fixture, 160mm*80mm*10mm aluminium alloy plate is cut out with wire cutting,
Then the aluminium alloy plate is fitted into CNC boards and rough mills inner chamber and locating dowel, then fix frame with fixture, finish inner chamber
Structure.Taking-up greasy dirt cleaning machine cleaning aluminum alloy frame, degreases after processing, and is then cleaned with deionized water dry
Only, dry in an oven.
The processing of aluminum alloy frame micropore
First above-mentioned aluminum alloy frame is put into 2%~10% sodium hydroxide solution, 40 DEG C of heating water baths are in 2~5 minutes,
Then cleaned up with deionized water；Then it will be put into 1%~10% salpeter solution, soak 3~10 minutes, after having soaked
Equally cleaned with deionized water；Then frame is put into electrolytic cell, contained in groove the hydrochloric acid into 0.5~2mol/L, 0.5~
1.0mol/L sulfuric acid, 0.5~1.0mol/L phosphoric acid mixed liquor add certain corrosion inhibiter as electrolyte, with side
Frame is as anode, and graphite is controlled in 0.10~0.30A/ as negative electrode, 20~40s of DC electrolysis, current density in electrolytic cell
cm2, tank liquor temperature control is at 40 DEG C；Then take out and immerse 5~10s of acetone, be then washed with deionized water net and dry.
Aluminum alloy frame and carbon fibre integrated are compound
By micropore processing frame be encased in 3D plastotype moulds, positioning fix, then by carbon fibre initial rinse fabric cut
Into 140mm*80mm, then by the carbon cloth cut, laying in scuncheon, and is put into 3D plastotype moulds according to demand
Row inner-cavity structure plastotype, 30~60s of plastotype then switch to hot-press solidifying in heat pressing forming machines, and solidification temperature is 135~150
DEG C, 40~60kg of pressure, solidify 10~15min, cooling mould to room temperature, take out the product inside mould and just obtain integral production
Product, then carry out inner frame structure again and finely polish to remove the epoxy resin that shaping is overflowed, you can it is fine to obtain aluminum alloy frame and carbon
Tie up integral composite rim.
By actual measurement, the carbon fiber metal composite airframe structural weight obtained by examples detailed above is 63g, compared with specification of the same race
But overall that 7g is about mitigated using the airframe structure weight (70g) of aluminium alloy center, the compression strength of deckle board wherein in carbon fiber
Compression strength (6.5MP power) than aluminium alloy center increases 2MP.
Above content is to combine specific/preferred embodiment further description made for the present invention, it is impossible to is recognized
The specific implementation of the fixed present 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, it can also make some replacements or modification to the embodiment that these have been described,
And these are substituted or variant should all be considered as belonging to protection scope of the present invention.
Claims (9)
1. a kind of carbon fiber metal composite electron product airframe structure, the electronic product body structure is handset structure,
It is characterised in that it includes aluminum alloy frame with the inside of the aluminum alloy frame, with the bluk recombination of aluminum alloy frame one
Deckle board in carbon fiber, the aluminum alloy frame have the microcellular structure formed through surface corrosion processing, deckle board in the carbon fiber
It is combined with the surface with the microcellular structure of the aluminum alloy frame, is molded as one through hot-press solidifying, the carbon is fine
Deckle board is handled and shape through 3D plastotypes and hot-press solidifying by carbon cloth of the laying on the inside of the aluminum alloy frame that interlock in dimension
Into carbon fiber structural.
2. carbon fiber metal composite electron product airframe structure as claimed in claim 1, it is characterised in that the hole of the micropore
Footpath is 20~100 nanometers, and the micropore is evenly distributed on aluminum alloy frame surface.
3. a kind of preparation method of carbon fiber metal composite electron product airframe structure, it is characterised in that comprise the following steps：
S1, prepare aluminum alloy frame；
S2, surface corrosion processing is carried out to the aluminum alloy frame so as to form micropore knot on the surface of the aluminum alloy frame
Structure；
S3, carbon cloth is placed on the inside of the aluminum alloy frame, 3D plastotypes and hot-press solidifying are carried out to the carbon cloth
Processing, deckle board in the carbon fiber being combined as a whole with the aluminum alloy frame is formed after processing, wherein the aluminum alloy frame leads to
Cross the surface with the microcellular structure and the hardened conjunction of carbon fiber center.
4. the preparation method of carbon fiber metal composite electron product airframe structure as claimed in claim 3, it is characterised in that step
In rapid S2, the surface corrosion processing includes electrochemical corrosion processing.
5. the preparation method of carbon fiber metal composite electron product airframe structure as claimed in claim 4, it is characterised in that institute
Electrochemical corrosion processing is stated using 0.5~2mol/L hydrochloric acid, 0.5~1.0mol/L sulfuric acid, 0.5~1.0mol/L phosphoric acid
Mixed liquor is as electrolyte.
6. the preparation method of carbon fiber metal composite electron product airframe structure as claimed in claim 5, it is characterised in that step
Rapid S2 includes：The aluminum alloy frame is put into the sodium hydroxide solution that mass concentration is 2%~10%, heating water bath 2~5
Minute, after cleaning, it is put into 1%~10% salpeter solution, soaks 3~10 minutes, after cleaning again, be put into electrolytic cell,
The hydrochloric acid into 0.5~2mol/L, 0.5~1.0mol/L sulfuric acid, 0.5~1.0mol/L phosphoric acid mixed liquor are contained in groove as electricity
Liquid is solved, and adds appropriate corrosion inhibiter, using the aluminum alloy frame as anode, graphite is as negative electrode using in electrolytic cell, directly
Stream 20~40s of electrolysis, current density are controlled in 0.10~0.30A/cm2, tank liquor temperature control is at 30~50 DEG C；After having handled
5~10s of acetone solution is immersed, cleans and dries afterwards.
7. the preparation method of the carbon fiber metal composite electron product airframe structure as described in any one of claim 3 to 6, it is special
Sign is that step S3 includes：Carbon cloth is cut into preliminary dimension, then the carbon cloth laying cut is closed in the aluminium
Golden scuncheon, for forming deckle board in the carbon fiber.
8. the preparation method of carbon fiber metal composite electron product airframe structure as claimed in claim 7, it is characterised in that step
Rapid S3 also includes：The good carbon cloth of laying and the aluminum alloy frame are put into 3D plastotype moulds, 30~60s of plastotype, so
After be transformed into heat pressing forming machines and carry out hot-press solidifying, solidification temperature is 135~150 DEG C, 40~60kg of pressure, solidification 10~
15min, then cool down.
9. the preparation method of the carbon fiber metal composite electron product airframe structure as described in any one of claim 3 to 6, it is special
Sign is, also includes after step S3：Polishing is carried out to molding structure and removes the epoxy resin overflowed after carbon cloth shaping.
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| 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 |
| 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 |
| CN106331236B (en) * | 2016-09-18 | 2019-06-04 | 广东劲胜智能集团股份有限公司 | A kind of titanium alloy plastic composite mobile phone frame and preparation method thereof |
| CN106363869B (en) * | 2016-10-25 | 2019-04-12 | 深圳市宝元金实业有限公司 | A method of nano aperture is formed in metallic substrate surface |
| 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 |
| 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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| 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 |
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| CN103297565B (en) * | 2012-02-24 | 2015-07-22 | 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 |
| CN103276435B (en) * | 2013-05-21 | 2014-08-06 | 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 |
| CN104411126B (en) * | 2014-11-14 | 2016-08-24 | 东莞劲胜精密组件股份有限公司 | A kind of electronic product casing and preparation method thereof |
| CN105128260B (en) * | 2015-09-30 | 2017-07-21 | 东莞市科泰汽车检夹具有限公司 | A kind of metal shell of electronic product and preparation method thereof |
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