CN102875966A - High-performance airplane empennage composite material and its preparation technology - Google Patents
High-performance airplane empennage composite material and its preparation technology Download PDFInfo
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- CN102875966A CN102875966A CN2011101962096A CN201110196209A CN102875966A CN 102875966 A CN102875966 A CN 102875966A CN 2011101962096 A CN2011101962096 A CN 2011101962096A CN 201110196209 A CN201110196209 A CN 201110196209A CN 102875966 A CN102875966 A CN 102875966A
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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
- B29C48/00—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor
- B29C48/25—Component parts, details or accessories; Auxiliary operations
- B29C48/36—Means for plasticising or homogenising the moulding material or forcing it through the nozzle or die
- B29C48/50—Details of extruders
- B29C48/505—Screws
- B29C48/625—Screws characterised by the ratio of the threaded length of the screw to its outside diameter [L/D ratio]
-
- 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
- B29C48/00—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor
- B29C48/25—Component parts, details or accessories; Auxiliary operations
- B29C48/36—Means for plasticising or homogenising the moulding material or forcing it through the nozzle or die
- B29C48/395—Means for plasticising or homogenising the moulding material or forcing it through the nozzle or die using screws surrounded by a cooperating barrel, e.g. single screw extruders
- B29C48/40—Means for plasticising or homogenising the moulding material or forcing it through the nozzle or die using screws surrounded by a cooperating barrel, e.g. single screw extruders using two or more parallel screws or at least two parallel non-intermeshing screws, e.g. twin screw extruders
-
- 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
- B29C48/00—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor
- B29C48/25—Component parts, details or accessories; Auxiliary operations
- B29C48/78—Thermal treatment of the extrusion moulding material or of preformed parts or layers, e.g. by heating or cooling
- B29C48/875—Thermal treatment of the extrusion moulding material or of preformed parts or layers, e.g. by heating or cooling for achieving a non-uniform temperature distribution, e.g. using barrels having both cooling and heating zones
-
- 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
- B29C48/00—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor
- B29C48/25—Component parts, details or accessories; Auxiliary operations
- B29C48/92—Measuring, controlling or regulating
-
- 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
- B29C2948/00—Indexing scheme relating to extrusion moulding
- B29C2948/92—Measuring, controlling or regulating
- B29C2948/92504—Controlled parameter
- B29C2948/9258—Velocity
- B29C2948/9259—Angular velocity
-
- 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
- B29C2948/00—Indexing scheme relating to extrusion moulding
- B29C2948/92—Measuring, controlling or regulating
- B29C2948/92504—Controlled parameter
- B29C2948/92704—Temperature
-
- 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
- B29C2948/00—Indexing scheme relating to extrusion moulding
- B29C2948/92—Measuring, controlling or regulating
- B29C2948/92819—Location or phase of control
- B29C2948/92857—Extrusion unit
- B29C2948/92876—Feeding, melting, plasticising or pumping zones, e.g. the melt itself
- B29C2948/92885—Screw or gear
-
- 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
- B29C2948/00—Indexing scheme relating to extrusion moulding
- B29C2948/92—Measuring, controlling or regulating
- B29C2948/92819—Location or phase of control
- B29C2948/92857—Extrusion unit
- B29C2948/92876—Feeding, melting, plasticising or pumping zones, e.g. the melt itself
- B29C2948/92895—Barrel or housing
Abstract
The invention discloses a high-performance airplane empennage composite material and its preparation technology. The special material of the composite material is prepared by adding 1-3 parts of processing assistants to 20-90 parts of PEEK (polyether-ether-ketone) and 10-50 parts CF (carbon fiber) which are adopted as main raw materials, wherein the composite material also comprises 0-30 parts of a graphite fiber. The preparation technology comprises the following steps: weighing the above raw materials according to the above proportions, carrying out surface treatment of the CF and the graphite fiber, adding through a special addition port, and carrying out blending extrusion in a double screw extruder. The high-performance airplane empennage composite material adopts mixed fibers to enhance the extraordinary engineering plastic polyether-ether-ketone composite material, so the airplane empennage composite material has the unique advantages of excellent fatigue resistance, moisture/heat resistance, creep deformation resistance, chemical resistance, self-extinguishing property, flame resistance, electrical insulation property and the like, can be widely applied to the aviation and spaceflight fields, can substitute aluminum, titanium and other metal materials to manufacture various internal and external parts of an airplane in order to reduce the weight of the airplane, and the lightweight parts have the advantages of easy assembling and the reduction of the whole cost of the airplane running.
Description
Technical field
The invention discloses a kind of high performance aircraft tail matrix material and preparation technology thereof.Be specifically related to a kind of blend fiber reinforced polyether ether ketone matrix material and preparation technology thereof who is applied to aircraft tail in the aerospace field.
Technical background
Aircraft tail divides vertical fin and tailplane, and vertical fin produces drifting moment, mainly plays aboard direction and stabilizes and directional control, and tailplane produces elevation moment, mainly plays vertically stable and pitch control.The security that aircraft tail aloft flies to aircraft has very important effect.
Advanced composite material has high than strong, Gao Bimo, antifatigue, multi-functional, anisotropy and designability, but the excellent properties such as identity of material and structure, since coming out the sixties in last century, advanced composite material obtains widespread use very soon, becomes one of aerospace four large materials.Boeing and Airbus SAS have adopted carbon-fibre composite to make the major part of agent structure, and have following advantage than traditional metallic material alloy: (1) quality is light; (2) excellent corrosion resistance; (3) resistance to fatigue is strong; (4) can reduce machining; (5) the shape part of energy processing and manufacturing complexity; (6) can place fortifying fibre towards the direction orientation of maximum rigidity and intensity; (7) can reduce assembly number and fixing number of packages; (8) matrix material radar and microwave absorbing are low, can provide stealthy ability to make radar be difficult to find; (9) thermal expansivity is low, reduces the possibility that operational issue occurs in the high-altitude vehicle.
The characteristic that matrix material is not of the common run, and the in recent years reduction of production cost have been accelerated the process that metallic substance changes to matrix material.The application of matrix material has the advantage that can make aircraft structure loss of weight and structure design cost.In the face of higher fuel price and more and more serious pollutant emission standard, matrix material can make the advantage of aircraft loss of weight particularly important.
Matrix material of the present invention has excellent anti-fatigue performance, moisture-proof/thermal characteristics, creep resistance, chemical resistance, self flame retardant resistance, electrical insulating property etc., is one of optimal material of making aircraft tail.
Summary of the invention
The present invention is some problems that exist in order to solve traditional metallic material alloy for the manufacture of aircraft tail, a kind of high performance aircraft tail matrix material and the preparation technology thereof of proposition.Technical scheme of the present invention is PEEK, 20～90 parts; CF, 40～50 parts; Graphite fibre, 0～30 part and processing aid, 1～3 part.Described its second-order transition temperature of PEEK polyether-ether-ketone resin is 200～240 ℃, and limiting viscosity is 1～5.Described carbon fiber is high-performance carbon fibre, average aspect ratio 8: 1～15: 1, tensile strength 3500～5000MPa, tensile modulus 200～500GPa.Described graphite fibre is asphalt series high-performance graphite fibre, tensile strength 1500～3500MPa, tensile modulus 500～900GPa.Described processing aid is one or more in lubricant, dispersion agent, the coupling agent.
A kind of high performance aircraft tail matrix material of the present invention and preparation technology thereof are as follows:
The process of surface treatment of carbon fiber and graphite fibre is sulfonated polyether-ether-ketone method, nitric acid normal temperature facture, nitration mixture ultrasonic oxidation method or high temperature nitric acid immersion method.Adopt carbon fiber and graphite fibre to mix and strengthen PEEK, at first that PEEK resin and processing aid is even in high-speed mixer and mixing, join in the twin screw extruder, and the CF after surface treatment and graphite fibre are added entrance from specialty add, carry out mixing, extrude, cooling, pelletizing, get the cylindrical pellet product.Extrude barrel temperature: 330～360 ℃ of back segments, 350～380 ℃ in stage casing, 360～400 ℃ of leading portions, screw slenderness ratio 15～25.
The present invention adopts high-performance carbon fibre and graphite fibre to mix enhancing PEEK, making this matrix material have the excellent properties such as high specific strength, high ratio modulus, wear-resisting, high temperature resistant, corrosion-resistant, antifatigue and thermal expansivity be little, is Developing Space aviation and the indispensable novel material of military sophisticated technology.Strengthen PEEK and independent graphite fibre enhancing PEEK than independent carbon fiber, it is all higher that carbon fiber and graphite fibre mix the every key property that strengthens the PEEK matrix material, this mainly is because carbon fiber and graphite fibre and PEEK matrix tackiness are very good, and have extraordinary synergistic effect between carbon fiber and the graphite fibre, can obviously improve the performance of matrix material.So, matrix material of the present invention has the various features such as high specific strength, high ratio modulus, excellent flame retardant resistance, wear resistance, electrical insulating property, alternative metallic substance is made aircraft tail, reach the purpose of loss of weight and minimizing oil consumption, and shaping speed is fast, a large amount of labor savings are a kind of development potentialities that have very much, the high performance composite that can widely popularize at aerospace field.
Embodiment:
The present invention is described in more detail below in conjunction with specific embodiment, but the present invention is not limited to each example of following enforcement:
Present embodiment is doubly grand twin screw extruder and sea day injection moulding machine of use section all; Main raw material is mainly the import material, and PEEK originates in Britain ICI company, and CF and graphite fibre all originate in U.S. Celanese Corp..
A kind of high performance aircraft tail matrix material of the present invention and preparation technology thereof are as follows:
The process of surface treatment of CF and graphite fibre is sulfonated polyether-ether-ketone method, nitric acid normal temperature facture, nitration mixture ultrasonic oxidation method or high temperature nitric acid immersion method.Adopt CF and graphite fibre to mix and strengthen PEEK, at first that PEEK resin and processing aid is even in high-speed mixer and mixing, join in the twin screw extruder, and the carbon fiber after surface treatment and graphite fibre are added entrance from specialty add, carry out mixing, extrude, cooling, pelletizing, get the cylindrical pellet product.Extrude barrel temperature: 330～360 ℃ of back segments, 350～380 ℃ in stage casing, 360～400 ℃ of leading portions, screw slenderness ratio 15～25, screw speed 200～800r/min.
Embodiments of the present invention are all carried out according to above technique, specific as follows shown in:
Embodiment 1
80 parts of PEEK resins and 2 parts of processing aids are mixed 2～5min through high-speed mixer, 20 parts of carbon fibers add entrance through specialty and add, mixing rear discharging joins in the twin screw extruder, mixing, extrude, cooling, pelletizing, get the cylindrical pellet product, the properties detected result is as shown in table 1 below.
Embodiment 2
70 parts of PEEK resins and 2 parts of processing aids are mixed 2～5min through high-speed mixer, 20 parts of carbon fibers and 10 parts of graphite fibres add entrance through specialty and add, mixing rear discharging joins in the twin screw extruder, mixing, extrude, cooling, pelletizing, get the cylindrical pellet product, the properties detected result is as shown in table 1 below.
Embodiment 3
60 parts of PEEK resins and 2 parts of processing aids are mixed 2～5min through high-speed mixer, 30 parts of carbon fibers and 10 parts of graphite fibres add entrance through specialty and add, mixing rear discharging joins in the twin screw extruder, mixing, extrude, cooling, pelletizing, get the cylindrical pellet product, the properties detected result is as shown in table 1 below.
Embodiment 4
70 parts of PEEK resins and 2 parts of processing aids are mixed 2～5min through high-speed mixer, 10 parts of carbon fibers and 20 parts of graphite fibres add entrance through specialty and add, mixing rear discharging joins in the twin screw extruder, mixing, extrude, cooling, pelletizing, get the cylindrical pellet product, the properties detected result is as shown in table 1 below.
Embodiment 5
60 parts of PEEK resins and 2 parts of processing aids are mixed 2～5min through high-speed mixer, 10 parts of carbon fibers and 30 parts of graphite fibres add entrance through specialty and add, mixing rear discharging joins in the twin screw extruder, mixing, extrude, cooling, pelletizing, get the cylindrical pellet product, the properties detected result is as shown in table 1 below.
Embodiment 6
60 parts of PEEK resins and 2 parts of processing aids are mixed 2～5min through high-speed mixer, 20 parts of carbon fibers and 20 parts of graphite fibres add entrance through specialty and add, mixing rear discharging joins in the twin screw extruder, mixing, extrude, cooling, pelletizing, get the cylindrical pellet product, the properties detected result is as shown in table 1 below.
The resulting blend fiber of above 6 embodiment is strengthened the PEEK matrix material, prepare the injection moulding batten according to same injecting condition.
Injecting condition: 350～450 ℃ of injection temperatures, 150～200 ℃ of die temperatures, injection pressure 1200～1800Kg/cm
2, keep to press 600～1000, injection speed is middling speed～at a high speed.
Each embodiment physicals is all tested by DIN and American National Standard, and concrete examination criteria is as follows:
Table 1
As can be seen from Table 1, along with the increase of fibre content, the shock strength of matrix material reduces thereupon, and tensile strength and flexural strength then increase thereupon.In addition, we from the table also as can be known, the carbon fiber of different ratios and graphite fibre strengthen PEEK, its performance is different, the composite material strength that carbon fiber content is high is high, the matrix material modulus that graphite fibre content is high is high, this mainly is because carbon fiber is higher than graphite fibre intensity, graphite fibre is higher than modulus of carbon fibres, so, select carbon fiber and graphite fibre to strengthen simultaneously PEEK, energy is both advantages comprehensively, obtain to have simultaneously high specific strength, the high performance composite of the excellent properties such as high ratio modulus satisfy the requirement of advanced composite material in the field of aerospace, wherein are especially suitable for use as the aircraft tail matrix material.To sum up, the prepared blend fiber of the present invention strengthens PEEK and has the excellent properties such as high specific strength, high ratio modulus, wear-resisting, high temperature resistant, corrosion-resistant, antifatigue and thermal expansivity be little, is a kind of highly desirable, indispensable advanced composite material.
Claims (8)
1. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof is characterized in that the performances such as high specific strength, high ratio modulus, antifatigue, and its component and content are as follows: PEEK (polyether-ether-ketone), 10～90 parts; CF (carbon fiber), 10～50 parts, graphite fibre, 0～30 part and processing aid, 1～3 part.
2. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof is characterized in that its second-order transition temperature of described polyether-ether-ketone resin is 200～240 ℃, and limiting viscosity is 1～5.
3. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof, it is characterized in that described carbon fiber is high-performance carbon fibre, average aspect ratio 8: 1～15: 1, tensile strength 3500～5000MPa, tensile modulus 200～500GPa.
4. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof is characterized in that described graphite fibre is asphalt series high-performance graphite fibre, tensile strength 1500～3500MPa, tensile modulus 500～900GPa.
5. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof is characterized in that described processing aid is one or more in lubricant, dispersion agent, the coupling agent.
6. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof, the process of surface treatment that it is characterized in that carbon fiber and graphite fibre is one or more in sulfonated polyether-ether-ketone method, nitric acid normal temperature facture, nitration mixture ultrasonic oxidation method and the high temperature nitric acid immersion method.
7. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof, it is characterized in that adopting carbon fibre and graphite fibre to mix and strengthen PEEK, at first that PEEK resin and processing aid is even in high-speed mixer and mixing, join in the twin screw extruder, and the CF after surface treatment and graphite fibre are added entrance from specialty add, carry out mixing, extrude, cooling, pelletizing, get the cylindrical pellet product.
8. a kind of high performance aircraft tail matrix material according to claim 1 and preparation technology thereof, it is characterized in that: extrude barrel temperature: 330～360 ℃ of back segments, 350～380 ℃ in stage casing, 360～400 ℃ of leading portions, screw slenderness ratio 15～25, screw speed 200～800r/min.
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| CN201110196209.6A CN102875966B (en) | 2011-07-13 | 2011-07-13 | A kind of high performance aircraft tail matrix material and preparation technology thereof |
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| CN201110196209.6A CN102875966B (en) | 2011-07-13 | 2011-07-13 | A kind of high performance aircraft tail matrix material and preparation technology thereof |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104191753A (en) * | 2014-08-27 | 2014-12-10 | 江苏呈飞精密合金股份有限公司 | Method for preparing continuous carbon fiber enhanced polyether-ether-ketone matrix fiber metal laminates |
| CN105524405A (en) * | 2015-11-03 | 2016-04-27 | 南京肯特复合材料有限公司 | Antistatic peek composite material and preparation method thereof |
| CN105733182A (en) * | 2014-12-10 | 2016-07-06 | 黑龙江鑫达企业集团有限公司 | Method for preparing high-performance polyetheretherketone/carbon fiber composite material |
| CN106189234A (en) * | 2016-07-13 | 2016-12-07 | 温州雏鹰科技有限公司 | A kind of high intensity unmanned plane propeller and preparation technology thereof |
| CN106182952A (en) * | 2016-07-13 | 2016-12-07 | 温州雏鹰科技有限公司 | A kind of high intensity unmanned plane wing and preparation method thereof |
| CN107828188A (en) * | 2017-11-30 | 2018-03-23 | 万丰航空工业有限公司 | A kind of manufacture method of carbon fibre composite for airplane skin |
| CN108034218A (en) * | 2018-01-17 | 2018-05-15 | 上海凝兰新材料科技有限公司 | A kind of ABS material for new-energy automobile empennage and preparation method thereof |
| CN110669311A (en) * | 2019-10-18 | 2020-01-10 | 吉林大学 | High-thermal-conductivity carbon fiber/polyether-ether-ketone electromagnetic shielding composite material |
| CN110669310A (en) * | 2019-10-18 | 2020-01-10 | 吉林大学 | High-thermal-conductivity polyether-ether-ketone electromagnetic shielding composite material and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1569931A (en) * | 2004-04-26 | 2005-01-26 | 东莞市正昱塑胶五金有限公司 | Fiber reinforced thermolplastic plastic preparation method |
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2011
- 2011-07-13 CN CN201110196209.6A patent/CN102875966B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1569931A (en) * | 2004-04-26 | 2005-01-26 | 东莞市正昱塑胶五金有限公司 | Fiber reinforced thermolplastic plastic preparation method |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104191753A (en) * | 2014-08-27 | 2014-12-10 | 江苏呈飞精密合金股份有限公司 | Method for preparing continuous carbon fiber enhanced polyether-ether-ketone matrix fiber metal laminates |
| CN105733182A (en) * | 2014-12-10 | 2016-07-06 | 黑龙江鑫达企业集团有限公司 | Method for preparing high-performance polyetheretherketone/carbon fiber composite material |
| CN105524405A (en) * | 2015-11-03 | 2016-04-27 | 南京肯特复合材料有限公司 | Antistatic peek composite material and preparation method thereof |
| CN106189234A (en) * | 2016-07-13 | 2016-12-07 | 温州雏鹰科技有限公司 | A kind of high intensity unmanned plane propeller and preparation technology thereof |
| CN106182952A (en) * | 2016-07-13 | 2016-12-07 | 温州雏鹰科技有限公司 | A kind of high intensity unmanned plane wing and preparation method thereof |
| CN106182952B (en) * | 2016-07-13 | 2018-06-29 | 温州雏鹰科技有限公司 | A kind of high intensity unmanned plane wing and preparation method thereof |
| CN107828188A (en) * | 2017-11-30 | 2018-03-23 | 万丰航空工业有限公司 | A kind of manufacture method of carbon fibre composite for airplane skin |
| CN108034218A (en) * | 2018-01-17 | 2018-05-15 | 上海凝兰新材料科技有限公司 | A kind of ABS material for new-energy automobile empennage and preparation method thereof |
| CN110669311A (en) * | 2019-10-18 | 2020-01-10 | 吉林大学 | High-thermal-conductivity carbon fiber/polyether-ether-ketone electromagnetic shielding composite material |
| CN110669310A (en) * | 2019-10-18 | 2020-01-10 | 吉林大学 | High-thermal-conductivity polyether-ether-ketone electromagnetic shielding composite material and preparation method thereof |
| CN110669310B (en) * | 2019-10-18 | 2021-06-08 | 吉林大学 | High-thermal-conductivity polyether-ether-ketone electromagnetic shielding composite material and preparation method thereof |
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