CN102875966B - A kind of high performance aircraft tail matrix material and preparation technology thereof - Google Patents
A kind of high performance aircraft tail matrix material and preparation technology thereof Download PDFInfo
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- CN102875966B CN102875966B CN201110196209.6A CN201110196209A CN102875966B CN 102875966 B CN102875966 B CN 102875966B CN 201110196209 A CN201110196209 A CN 201110196209A CN 102875966 B CN102875966 B CN 102875966B
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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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Compositions Of Macromolecular Compounds (AREA)
Abstract
The present invention discloses a kind of high performance aircraft tail matrix material and preparation technology thereof.PP Pipe Compound be with PEEK (polyether-ether-ketone), CF (carbon fiber) for main raw material, add the preparation of appropriate processing aid and obtain, wherein PEEK, 20 ~ 90 parts; CF, 10 ~ 50 parts; Graphite fibre, 0 ~ 30 part and processing aid, 1 ~ 3 part.Take raw material according to the above ratio, add entrance through specialty after surface treatment is carried out to CF and graphite fibre and add, blending extrusion on the twin screw extruder.High performance airplane empennage matrix material of the present invention strengthens special engineering plastics polyether-ether-ketone composite material owing to have employed blend fiber, there is unique advantage, as the anti-fatigue performance, moisture-proof/thermal characteristics, creep resistance, chemical resistance, self-extinguishing, flame retardant resistance, electrical insulating property etc. of excellence, be widely used in aerospace field, aluminium, titanium and other metallic substance can be replaced to manufacture various aircraft inside and outside portion part, reduce aircraft weight, lightweight component means and easily assemble and reduce the holistic cost of aircraft operation.
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 the blend fiber reinforced polyether ether ketone matrix material and the preparation technology thereof that are applied to aircraft tail in aerospace field.
Technical background
Aircraft tail divides vertical fin and tailplane, and vertical fin produces drifting moment, mainly plays direction aboard and stabilizes and directional control, and tailplane produces elevation moment, mainly plays longitudinally stable and pitch control.Aircraft tail has very important effect to the security that aircraft flies aloft.
Advanced composite material has high than strong, Gao Bimo, antifatigue, multi-functional, anisotropy and designability, material and structure can the excellent properties such as identity, since the sixties in last century comes out, advanced composite material obtains widespread use very soon, becomes one of large material of aerospace four.Boeing and Airbus SAS have adopted carbon-fibre composite to manufacture the major part of agent structure, have the following advantages: (1) quality is light compared to traditional metallic material alloy tool; (2) excellent corrosion resistance; (3) resistance to fatigue is strong; (4) can reduce engine process; (5) profiles of energy processing and manufacturing complexity; (6) fortifying fibre can be placed towards the direction orientation of maximum rigidity and intensity; (7) assembly number and fixing number of packages can be reduced; (8) matrix material radar and microwave-absorbing low, can provide stealthy ability to be difficult to find to make radar; (9) thermal expansivity is low, reduces the possibility that operational issue occurs in high-altitude vehicle.
The characteristic that matrix material is not of the common run, and the reduction of production cost in recent years, accelerate the process that metallic substance changes to matrix material.The application of matrix material has the advantage that aircraft structure loss of weight and structure design cost can be made to reduce.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 retardance, electrical insulating property etc., is one of optimal material manufacturing aircraft tail.
Summary of the invention
The present invention is some problems existed to solve traditional metallic material alloy for the manufacture of aircraft tail, the high performance aircraft tail matrix material of one of proposition and preparation technology thereof.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 DEG C, 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 fiber, tensile strength 1500 ~ 3500MPa, tensile modulus 500 ~ 900GPa.Described processing aid is one or more in lubricant, dispersion agent, coupling agent.
One of the present invention high performance aircraft tail matrix material and preparation technology 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.Carbon fiber and graphite fibre mixing is adopted to strengthen PEEK, first by PEEK resin and processing aid even in high-speed mixer and mixing, join in twin screw extruder, and the CF after surface treatment and graphite fibre are added entrance from specialty add, carry out mixing, extrude, cool, pelletizing, obtain cylindrical pellet product.Extrude barrel temperature: back segment 330 ~ 360 DEG C, 350 ~ 380 DEG C, stage casing, leading portion 360 ~ 400 DEG C, screw slenderness ratio 15 ~ 25.
The present invention adopts high-performance carbon fibre and graphite fibre mixing to strengthen PEEK, this matrix material the is had excellent properties such as high specific strength, high ratio modulus, wear-resisting, high temperature resistant, corrosion-resistant, antifatigue and thermal expansivity be little is the indispensable novel material of Developing Space aviation and military sophisticated technology.PEEK is strengthened compared to independent fibre reinforced PEEK and independent graphite fibre, every key property that carbon fiber and graphite fibre mixing strengthen PEEK matrix material is all higher, this mainly because carbon fiber and graphite fibre and PEEK matrix tackiness very good, and between carbon fiber and graphite fibre, there is extraordinary synergistic effect, the performance of matrix material can be significantly improved.So, matrix material of the present invention has high specific strength, high ratio modulus, the excellent various features such as flame retardant resistance, wear resistance, electrical insulating property, alternative metallic substance manufactures aircraft tail, reach the object of loss of weight and minimizing oil consumption, and shaping speed is fast, a large amount of saving labor force is that one very has development potentiality, the high performance composite can widelyd popularize at aerospace field.
Embodiment:
Below in conjunction with specific embodiment, the present invention is described in more detail, but the present invention is not limited to each example of following enforcement:
Present embodiment is use section doubly grand twin screw extruder and extra large sky injection moulding machine all; Main raw material is mainly import material, and PEEK originates in ICI company of Britain, and CF and graphite fibre all originate in Celanese Corp. of the U.S..
One of the present invention high performance aircraft tail matrix material and preparation technology 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.CF and graphite fibre mixing is adopted to strengthen PEEK, first by PEEK resin and processing aid even in high-speed mixer and mixing, join in twin screw extruder, and the carbon fiber after surface treatment and graphite fibre are added entrance from specialty add, carry out mixing, extrude, cool, pelletizing, obtain cylindrical pellet product.Extrude barrel temperature: back segment 330 ~ 360 DEG C, 350 ~ 380 DEG C, stage casing, leading portion 360 ~ 400 DEG C, screw slenderness ratio 15 ~ 25, screw speed 200 ~ 800r/min.
Embodiments of the present invention are all carried out, shown in specific as follows according to above technique:
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 twin screw extruder, mixing, extrude, cool, pelletizing, obtain cylindrical pellet product, 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 twin screw extruder, mixing, extrude, cool, pelletizing, obtain cylindrical pellet product, 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 twin screw extruder, mixing, extrude, cool, pelletizing, obtain cylindrical pellet product, 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 twin screw extruder, mixing, extrude, cool, pelletizing, obtain cylindrical pellet product, 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 twin screw extruder, mixing, extrude, cool, pelletizing, obtain cylindrical pellet product, 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 twin screw extruder, mixing, extrude, cool, pelletizing, obtain cylindrical pellet product, properties detected result is as shown in table 1 below.
The blend fiber above 6 embodiments obtained strengthens PEEK matrix material, prepares injection moulding batten according to same injecting condition.
Injecting condition: injection temperature 350 ~ 450 DEG C, die temperature 150 ~ 200 DEG C, injection pressure 1200 ~ 1800Kg/cm
2, keep pressure 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 are also known from table, 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, mainly because of carbon fiber, comparatively graphite fibre intensity is higher for this, graphite fibre comparatively modulus of carbon fibres is higher, so, select carbon fiber and graphite fibre to strengthen PEEK simultaneously, can both advantage comprehensive, obtain and there is high specific strength simultaneously, the high performance composite of the excellent properties such as high ratio modulus, meet the requirement of advanced composite material in field of aerospace, wherein be especially suitable for use as aircraft tail matrix material.To sum up, blend fiber prepared by 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 (4)
1. the preparation technology of a high performance aircraft tail matrix material, it is characterized in that, described aircraft tail matrix material has the performances such as high specific strength, high ratio modulus, antifatigue, its component and content as follows: PEEK (polyether-ether-ketone), 20 ~ 90 parts; CF (carbon fiber), 40 ~ 50 parts, graphite fibre, 10 ~ 30 parts and processing aid, 1 ~ 3 part;
Its second-order transition temperature of described polyether-ether-ketone resin is 200 ~ 240 DEG C, and limiting viscosity is 1 ~ 5;
The preparation technology of described aircraft tail matrix material is as follows:
The process of surface treatment of described 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 high temperature nitric acid immersion method; Carbon fibre and graphite fibre mixing is adopted to strengthen PEEK, first by PEEK resin and processing aid even in high-speed mixer and mixing, join in twin screw extruder, and the CF after surface treatment and graphite fibre are added entrance from specialty add, carry out mixing, extrude, cool, pelletizing, obtain cylindrical pellet product; Extrude barrel temperature: back segment 330 ~ 360 DEG C, 350 ~ 380 DEG C, stage casing, leading portion 360 ~ 400 DEG C, screw slenderness ratio 15 ~ 25, screw speed 200 ~ 800r/min.
2. according to the preparation technology of a kind of high performance aircraft tail matrix material described in claim 1, 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.
3., according to the preparation technology of a kind of high performance aircraft tail matrix material described in claim 1, it is characterized in that described graphite fibre is asphalt series high performance graphite fiber, tensile strength 1500 ~ 3500MPa, tensile modulus 500 ~ 900GPa.
4., according to the preparation technology of a kind of high performance aircraft tail matrix material described in claim 1, it is characterized in that described processing aid is one or more in lubricant, dispersion agent, coupling agent.
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN102875966B true CN102875966B (en) | 2015-08-26 |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| 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 |
| CN110669311B (en) * | 2019-10-18 | 2021-06-08 | 吉林大学 | High-thermal-conductivity carbon fiber/polyether-ether-ketone electromagnetic shielding composite material |
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 |
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| 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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