CN106746689B - It is a kind of applied to General Aviation in terms of glass fiber compound material and preparation method thereof - Google Patents
It is a kind of applied to General Aviation in terms of glass fiber compound material and preparation method thereof Download PDFInfo
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- CN106746689B CN106746689B CN201611096425.2A CN201611096425A CN106746689B CN 106746689 B CN106746689 B CN 106746689B CN 201611096425 A CN201611096425 A CN 201611096425A CN 106746689 B CN106746689 B CN 106746689B
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- C—CHEMISTRY; METALLURGY
- C03—GLASS; MINERAL OR SLAG WOOL
- C03C—CHEMICAL COMPOSITION OF GLASSES, GLAZES OR VITREOUS ENAMELS; SURFACE TREATMENT OF GLASS; SURFACE TREATMENT OF FIBRES OR FILAMENTS MADE FROM GLASS, MINERALS OR SLAGS; JOINING GLASS TO GLASS OR OTHER MATERIALS
- C03C13/00—Fibre or filament compositions
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- C—CHEMISTRY; METALLURGY
- C03—GLASS; MINERAL OR SLAG WOOL
- C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
- C03B37/00—Manufacture or treatment of flakes, fibres, or filaments from softened glass, minerals, or slags
- C03B37/01—Manufacture of glass fibres or filaments
- C03B37/02—Manufacture of glass fibres or filaments by drawing or extruding, e.g. direct drawing of molten glass from nozzles; Cooling fins therefor
- C03B37/022—Manufacture of glass fibres or filaments by drawing or extruding, e.g. direct drawing of molten glass from nozzles; Cooling fins therefor from molten glass in which the resultant product consists of different sorts of glass or is characterised by shape, e.g. hollow fibres, undulated fibres, fibres presenting a rough surface
-
- C—CHEMISTRY; METALLURGY
- C03—GLASS; MINERAL OR SLAG WOOL
- C03C—CHEMICAL COMPOSITION OF GLASSES, GLAZES OR VITREOUS ENAMELS; SURFACE TREATMENT OF GLASS; SURFACE TREATMENT OF FIBRES OR FILAMENTS MADE FROM GLASS, MINERALS OR SLAGS; JOINING GLASS TO GLASS OR OTHER MATERIALS
- C03C25/00—Surface treatment of fibres or filaments made from glass, minerals or slags
- C03C25/10—Coating
- C03C25/24—Coatings containing organic materials
- C03C25/40—Organo-silicon compounds
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- Engineering & Computer Science (AREA)
- Geochemistry & Mineralogy (AREA)
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- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- General Life Sciences & Earth Sciences (AREA)
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- Reinforced Plastic Materials (AREA)
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Abstract
Glass fiber compound material in terms of the invention discloses a kind of applied to General Aviation, the raw material including following parts by weight: 40-60 parts of silica, 1-6 parts of silicon carbide, 2-5 parts of polypropylene, 3-7 parts of barium titanate, 4-10 parts of potassium oxide, 4-7 parts of aluminium oxide, 2-10 parts of calcium oxide, 1-3 parts of magnesia, 1-5 parts of sodium oxide molybdena, 2-8 parts of barium monoxide, 1-4 parts of titanium dioxide, 20-40 parts of polyether-ether-ketone, 1-10 parts of dimethyl dichlorosilane (DMCS), 1-3 parts of t etram-ethyltetravinylcyclotetrasiloxane；Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, the following steps are included: S1, weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, calcium oxide, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide according to deal proportion.Glass fiber compound material intensity produced by the present invention is high, good heat insulating, can effectively reduce radiation, can be widely applied to aviation field.
Description
Technical field
The present invention relates to glass fiber compound material technical field more particularly to it is a kind of applied to General Aviation in terms of glass
Glass fibrous composite and preparation method thereof.
Background technique
Glass fibre belongs to inorganic non-metallic material, and with good insulating, heat resistance is strong, corrosion resistance is good, mechanical strength
Many advantages, such as high, it is to manufacture using glass marble or post-consumer glass as raw material through techniques such as high temperature melting, wire drawing, doff, woven fabrics
At, the diameter of monofilament is several microns to twenties meters microns, is equivalent to the 1/20-1/5 of a hairline, every beam is fine
Dimension precursor is all made of hundreds of even thousands of monofilament.Glass fibre is typically used as the reinforcing material in composite material, and electricity is absolutely
Edge material and heat-insulating material, the national economy every field such as circuit substrate, but existing glass fiber compound material is acidproof
It is alkaline, rigid, anti-aging, antioxygenic property is all to be improved, in aviation field using less, aerospace field is to composite wood
That expects is more demanding, needs to meet its strict requirements in terms of intensity, heat preservation, reduction radiation, we have proposed one kind thus
Glass fiber compound material in terms of applied to General Aviation and preparation method thereof.
Summary of the invention
Technical problems based on background technology, the glass fibers in terms of the invention proposes a kind of applied to General Aviation
Tie up composite material and preparation method.
It is proposed by the present invention it is a kind of applied to General Aviation in terms of glass fiber compound material, including following parts by weight
Raw material: 40-60 parts of silica, 1-6 parts of silicon carbide, 2-5 parts of polypropylene, 3-7 parts of barium titanate, 4-10 parts of potassium oxide, aluminium oxide
4-7 parts, 2-10 parts of calcium oxide, 1-3 parts of magnesia, 1-5 parts of sodium oxide molybdena, 2-8 parts of barium monoxide, 1-4 parts of titanium dioxide, polyether-ether-ketone
20-40 parts, 1-10 parts of dimethyl dichlorosilane (DMCS), 1-3 parts of t etram-ethyltetravinylcyclotetrasiloxane.
Preferably, the raw material including following parts by weight: 45-55 parts of silica, 2-5 parts of silicon carbide, 3-4 parts of polypropylene,
4-6 parts of barium titanate, 5-9 parts of potassium oxide, 5-6 parts of aluminium oxide, 4-8 parts of calcium oxide, 1.5-2.5 parts of magnesia, 2-4 parts of sodium oxide molybdena,
3-7 parts of barium monoxide, 2-3 parts of titanium dioxide, 25-35 parts of polyether-ether-ketone, 3-7 parts of dimethyl dichlorosilane (DMCS), tetramethyl tetravinyl ring
1.5-2.5 parts of tetrasiloxane.
Preferably, the raw material including following parts by weight: 50 parts of silica, 3 parts of silicon carbide, 3.5 parts of polypropylene, barium titanate
5 parts, 7 parts of potassium oxide, 5.5 parts of aluminium oxide, 6 parts of calcium oxide, 2 parts of magnesia, 3 parts of sodium oxide molybdena, 5 parts of barium monoxide, titanium dioxide 2.5
Part, 30 parts of polyether-ether-ketone, 5 parts of dimethyl dichlorosilane (DMCS), 2 parts of t etram-ethyltetravinylcyclotetrasiloxane.
Preferably, the silica, silicon carbide, polyacrylic weight ratio are 45-55:2-5:3-4.
Preferably, the barium titanate, potassium oxide, aluminium oxide weight ratio be 4-6:5-9:5-6.
Preferably, the calcium oxide, magnesia, sodium oxide molybdena weight ratio be 4-8:1.5-2.5:2-4.
Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, including with
Lower step:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, oxidation according to deal proportion
Above-mentioned raw materials are sequentially placed into reaction kettle by calcium, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide, in 100-120 DEG C of temperature
Under, being sufficiently stirred is uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl are added into glass metal
Cyclotetrasiloxane carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues under the protection of nitrogen
10-48h is cleaned 2-6 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre
Composite material.
Preferably, in the S5, dry temperature is 90-110 DEG C, continues 3-10min.
In the present invention, according to stringent ratio by silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide,
Calcium oxide, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide raw material are prepared, and add four ethylene of polyether-ether-ketone and tetramethyl
Basic ring tetrasiloxane carries out mechanical blending, can obtain the glass fiber compound material of higher intensity, mechanical property obtains pole
It is big to be promoted, silanization treatment is carried out using surface of the dimethyl dichlorosilane (DMCS) to primary filament, improves glass fiber compound material
Comprehensive performance, preparation method of the invention is simple, good manufacturability, the glass fiber compound material intensity height of preparation, thermal insulation property
It is good, radiation can be effectively reduced, can be widely applied to aviation field.
Specific embodiment
Combined with specific embodiments below the present invention is made further to explain.
Embodiment one
It is proposed by the present invention it is a kind of applied to General Aviation in terms of glass fiber compound material, including following parts by weight
Raw material: 40 parts of silica, 1 part of silicon carbide, 2 parts of polypropylene, 3 parts of barium titanate, 4 parts of potassium oxide, 4 parts of aluminium oxide, calcium oxide 2
Part, 1 part of magnesia, 1 part of sodium oxide molybdena, 2 parts of barium monoxide, 1 part of titanium dioxide, 20 parts of polyether-ether-ketone, 1 part of dimethyl dichlorosilane (DMCS), four
1 part of methyl tetravinyl cyclotetrasiloxane.
Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, including with
Lower step:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, oxidation according to deal proportion
Above-mentioned raw materials are sequentially placed into reaction kettle by calcium, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide, 100 DEG C at a temperature of, fill
Divide stirring to be uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl are added into glass metal
Cyclotetrasiloxane carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues under the protection of nitrogen
10h is cleaned 2 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre
Composite material.
Embodiment two
It is proposed by the present invention it is a kind of applied to General Aviation in terms of glass fiber compound material, including following parts by weight
Raw material: 45 parts of silica, 2 parts of silicon carbide, 3 parts of polypropylene, 4 parts of barium titanate, 5 parts of potassium oxide, 5 parts of aluminium oxide, calcium oxide 4
Part, 1.5 parts of magnesia, 2 parts of sodium oxide molybdena, 3 parts of barium monoxide, 2 parts of titanium dioxide, 25 parts of polyether-ether-ketone, 3 parts of dimethyl dichlorosilane (DMCS),
1.5 parts of t etram-ethyltetravinylcyclotetrasiloxane.
Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, including with
Lower step:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, oxidation according to deal proportion
Above-mentioned raw materials are sequentially placed into reaction kettle by calcium, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide, 105 DEG C at a temperature of, fill
Divide stirring to be uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl are added into glass metal
Cyclotetrasiloxane carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues under the protection of nitrogen
18h is cleaned 3 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre
Composite material.
Embodiment three
It is proposed by the present invention it is a kind of applied to General Aviation in terms of glass fiber compound material, including following parts by weight
Raw material: 50 parts of silica, 3 parts of silicon carbide, 3.5 parts of polypropylene, 5 parts of barium titanate, 7 parts of potassium oxide, 5.5 parts of aluminium oxide, oxidation
6 parts of calcium, 2 parts of magnesia, 3 parts of sodium oxide molybdena, 5 parts of barium monoxide, 2.5 parts of titanium dioxide, 30 parts of polyether-ether-ketone, dimethyl dichlorosilane (DMCS) 5
Part, 2 parts of t etram-ethyltetravinylcyclotetrasiloxane.
Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, including with
Lower step:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, oxidation according to deal proportion
Above-mentioned raw materials are sequentially placed into reaction kettle by calcium, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide, 110 DEG C at a temperature of, fill
Divide stirring to be uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl are added into glass metal
Cyclotetrasiloxane carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues under the protection of nitrogen
30h is cleaned 4 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre
Composite material.
Example IV
It is proposed by the present invention it is a kind of applied to General Aviation in terms of glass fiber compound material, including following parts by weight
Raw material: 55 parts of silica, 5 parts of silicon carbide, 4 parts of polypropylene, 6 parts of barium titanate, 9 parts of potassium oxide, 6 parts of aluminium oxide, calcium oxide 8
Part, 2.5 parts of magnesia, 4 parts of sodium oxide molybdena, 7 parts of barium monoxide, 3 parts of titanium dioxide, 35 parts of polyether-ether-ketone, 7 parts of dimethyl dichlorosilane (DMCS),
2.5 parts of t etram-ethyltetravinylcyclotetrasiloxane.
Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, including with
Lower step:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, oxidation according to deal proportion
Above-mentioned raw materials are sequentially placed into reaction kettle by calcium, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide, 115 DEG C at a temperature of, fill
Divide stirring to be uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl are added into glass metal
Cyclotetrasiloxane carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues under the protection of nitrogen
38h is cleaned 5 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre
Composite material.
Embodiment five
It is proposed by the present invention it is a kind of applied to General Aviation in terms of glass fiber compound material, including following parts by weight
Raw material: 60 parts of silica, 6 parts of silicon carbide, 5 parts of polypropylene, 7 parts of barium titanate, 10 parts of potassium oxide, 7 parts of aluminium oxide, calcium oxide 10
Part, 3 parts of magnesia, 5 parts of sodium oxide molybdena, 8 parts of barium monoxide, 4 parts of titanium dioxide, 40 parts of polyether-ether-ketone, 10 parts of dimethyl dichlorosilane (DMCS), four
3 parts of methyl tetravinyl cyclotetrasiloxane.
Glass fiber compound material preparation method in terms of the invention also provides a kind of applied to General Aviation, including with
Lower step:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, oxidation according to deal proportion
Above-mentioned raw materials are sequentially placed into reaction kettle by calcium, magnesia, sodium oxide molybdena, barium monoxide, titanium dioxide, 120 DEG C at a temperature of, fill
Divide stirring to be uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl are added into glass metal
Cyclotetrasiloxane carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues under the protection of nitrogen
48h is cleaned 6 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre
Composite material.
Glass fiber compound material prepared by embodiment three is compared detection with simple glass fibrous composite, is tied
Fruit is as shown in the table:
As seen from the above table, glass fiber compound material intensity height produced by the present invention, good heat insulating, can effectively reduce spoke
It penetrates, can be widely applied to aviation field.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (8)
1. it is a kind of applied to General Aviation in terms of glass fiber compound material, which is characterized in that the original including following parts by weight
Material: 40-60 parts of silica, 1-6 parts of silicon carbide, 2-5 parts of polypropylene, 3-7 parts of barium titanate, 4-10 parts of potassium oxide, aluminium oxide 4-7
Part, 2-10 parts of calcium oxide, 1-3 parts of magnesia, 1-5 parts of sodium oxide molybdena, 2-8 parts of barium monoxide, 1-4 parts of titanium dioxide, polyether-ether-ketone 20-
40 parts, 1-10 parts of dimethyl dichlorosilane (DMCS), 1-3 parts of t etram-ethyltetravinylcyclotetrasiloxane.
2. it is according to claim 1 it is a kind of applied to General Aviation in terms of glass fiber compound material, which is characterized in that
Raw material including following parts by weight: 45-55 parts of silica, 2-5 parts of silicon carbide, 3-4 parts of polypropylene, 4-6 parts of barium titanate, oxidation
5-9 parts of potassium, 5-6 parts of aluminium oxide, 4-8 parts of calcium oxide, 1.5-2.5 parts of magnesia, 2-4 parts of sodium oxide molybdena, 3-7 parts of barium monoxide, dioxy
Change titanium 2-3 parts, 25-35 parts of polyether-ether-ketone, 3-7 parts of dimethyl dichlorosilane (DMCS), t etram-ethyltetravinylcyclotetrasiloxane 1.5-2.5
Part.
3. it is according to claim 1 it is a kind of applied to General Aviation in terms of glass fiber compound material and its preparation side
Method, which is characterized in that the raw material including following parts by weight: 50 parts of silica, 3 parts of silicon carbide, 3.5 parts of polypropylene, barium titanate 5
Part, 7 parts of potassium oxide, 5.5 parts of aluminium oxide, 6 parts of calcium oxide, 2 parts of magnesia, 3 parts of sodium oxide molybdena, 5 parts of barium monoxide, titanium dioxide 2.5
Part, 30 parts of polyether-ether-ketone, 5 parts of dimethyl dichlorosilane (DMCS), 2 parts of t etram-ethyltetravinylcyclotetrasiloxane.
4. it is according to claim 1 it is a kind of applied to General Aviation in terms of glass fiber compound material, which is characterized in that
The silica, silicon carbide, polyacrylic weight ratio are 45-55:2-5:3-4.
5. it is according to claim 1 it is a kind of applied to General Aviation in terms of glass fiber compound material, which is characterized in that
The barium titanate, potassium oxide, aluminium oxide weight ratio be 4-6:5-9:5-6.
6. it is according to claim 1 it is a kind of applied to General Aviation in terms of glass fiber compound material, which is characterized in that
The calcium oxide, magnesia, sodium oxide molybdena weight ratio be 4-8:1.5-2.5:2-4.
7. it is a kind of applied to General Aviation in terms of glass fiber compound material preparation method, which is characterized in that including following step
It is rapid:
S1 weighs silica, silicon carbide, polypropylene, barium titanate, potassium oxide, aluminium oxide, calcium oxide, oxygen according to deal proportion
Change magnesium, sodium oxide molybdena, barium monoxide, titanium dioxide, above-mentioned raw materials are sequentially placed into reaction kettle, 100-120 DEG C at a temperature of, sufficiently
Stirring is uniformly mixed it, obtains mixture A；
Mixture A in S1 is fused into glass metal by S2, and polyether-ether-ketone and tetramethyl tetravinyl ring four are added into glass metal
Siloxanes carries out mechanical blending, obtains mixed liquid B；
Primary filament is made by wire drawing in mixed liquid B in S2 by S3；
S4 carries out silanization treatment using surface of the dimethyl dichlorosilane (DMCS) to primary filament, continues 10- under the protection of nitrogen
48h is cleaned 2-6 times using aqueous acetone solution；
Primary filament after being cleaned in S5, dry S4, can be obtained it is a kind of applied to General Aviation in terms of glass fibre it is compound
Material.
8. it is according to claim 7 it is a kind of applied to General Aviation in terms of glass fiber compound material preparation method,
It is characterized in that, in the S5, dry temperature is 90-110 DEG C, continues 3-10min.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201611096425.2A CN106746689B (en) | 2016-12-02 | 2016-12-02 | It is a kind of applied to General Aviation in terms of glass fiber compound material and preparation method thereof |
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| CN201611096425.2A CN106746689B (en) | 2016-12-02 | 2016-12-02 | It is a kind of applied to General Aviation in terms of glass fiber compound material and preparation method thereof |
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| CN106746689B true CN106746689B (en) | 2019-05-14 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101636360A (en) * | 2007-03-15 | 2010-01-27 | 日本电气硝子株式会社 | Glass composition for glass fiber, glass fiber, process for producing glass fiber and composite material |
| CN103086605A (en) * | 2013-02-19 | 2013-05-08 | 重庆国际复合材料有限公司 | Glass fiber |
-
2016
- 2016-12-02 CN CN201611096425.2A patent/CN106746689B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101636360A (en) * | 2007-03-15 | 2010-01-27 | 日本电气硝子株式会社 | Glass composition for glass fiber, glass fiber, process for producing glass fiber and composite material |
| CN103086605A (en) * | 2013-02-19 | 2013-05-08 | 重庆国际复合材料有限公司 | Glass fiber |
Non-Patent Citations (1)
| Title |
|---|
| "玻璃纤维增强聚丙烯复合材料力学性能的研究进展";曾彪;《上海塑料》;20150630;第11，13页 |
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Address after: Jiaozhou City, Shandong province 266300 Qingdao City Huiying economic and Technological Development Zone, South First Street Applicant after: Qingdao Branch Co., Ltd. of Mechanical Science Research Institute Address before: Jiaozhou City, Shandong province 266300 Qingdao City Huiying economic and Technological Development Zone, South First Street Applicant before: Qingdao Branch of General Research Institute of Mechanical Science |
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Address after: 266300 South Head of Huiying Street, Jiaozhou Economic and Technological Development Zone, Qingdao City, Shandong Province Patentee after: China National Academy of Machinery Group Qingdao Branch Co.,Ltd. Address before: 266300 South Head of Huiying Street, Jiaozhou Economic and Technological Development Zone, Qingdao City, Shandong Province Patentee before: Qingdao Branch Co., Ltd. of Mechanical Science Research Institute |