CN109796759A - A kind of high thermal conductivity coefficient cyanate base carbon fiber composite material and preparation method thereof - Google Patents
A kind of high thermal conductivity coefficient cyanate base carbon fiber composite material and preparation method thereof Download PDFInfo
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- CN109796759A CN109796759A CN201711137242.5A CN201711137242A CN109796759A CN 109796759 A CN109796759 A CN 109796759A CN 201711137242 A CN201711137242 A CN 201711137242A CN 109796759 A CN109796759 A CN 109796759A
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Abstract
The present invention relates to polymer matrix composites technical fields, specifically disclose a kind of space optics structure high thermal conductivity coefficient cyanate base carbon fiber composite material and preparation method thereof.Composite material of the invention includes cyanate/carbon fibre composite main body and high thermal conductivity functional layer, and high thermal conductivity functional layer is covered in cyanate/carbon fibre composite main body.Composite material of the invention includes cyanate/carbon fibre composite main body and high thermal conductivity functional layer, high thermal conductivity filer content is high and consistent with cyanate/matrix of carbon fibre composite main body in high thermal conductivity functional layer, there is no interface problems, the temperature uniformity that sensor etc. can be improved for space optics structure, the temperature gradient for improving lower thermal conductivity structural member on space optical remote sensor are of great significance.
Description
Technical field
The present invention relates to polymer matrix composites technical field, in particular to a kind of space optics structure high thermal conductivity coefficient
Cyanate base carbon fiber composite material and preparation method thereof.
Background technique
High performance composite material has indispensable status in aerospace field, with steel, titanium alloy and aluminium alloy
Support aerospace career development jointly.It is because having lightweight, high-modulus, high intensity, high tenacity, corrosion-resistant, weatherability etc.
Excellent properties and be able to show one's capabilities in this high-tech sector of aerospace.But due to being applied to aerospace and military affairs
The device in field is typically necessary to be run in harsh environments, such as high frequency, high power, high pressure and high temperature, and requires tool
There is high reliability, safety is long, also high to cooling requirements.Therefore higher want also proposed to the thermal conductivity of polymer composites
It asks.In order to defend the status of polymer composites, excellent combination property is developed, especially with the composite wood of high-termal conductivity
Material has become the most important thing.
Improve polymer bond's property economy and effective method is addition heat filling.By filling heat filling, polymerization
The thermal conductivity of object can increase substantially, and the polymer composites of different heating conduction requirements can be made.CN102766309A
Disclose the formula and its acquisition methods of a kind of filling-modified polytetrafluoroethylene (PTFE) high-heat-conductive composite material, graphite-filled parts by volume
Number is 18 ± 0.5%, and carbon fiber packing volume score is 10%.But the main problem of filled polymer base heat conducting material be with
The increase of conducting filler content, the raising of composite material heating conduction unavoidably bring the deterioration of material mechanical performance.
Therefore, in order to be on the actual application Heat Conduction Material, often using the heating conduction for reducing composite material as cost, in this way must
So limit the heating conduction and service performance of Heat Conduction Material.
What the conduction of heat in the composite relied on is the formation in phonon thermal conduction channel, inevitably by many
The interface of polymer and filler increases interface bond strength between the two, is conducive to the heating conduction for improving composite material.But it is general
Compatibility is very poor between inorganic filler particle and polymer resin matrix interface, and filler grain is difficult to be dispersed in resin matrix
In, and reunion easy to form, the difference of surface both tension makes interface there are gap at the same time, cannot be effectively reduced interface
Thermal resistance, then with carbon fiber formed composite material after, interfacial effect is more obvious.
Summary of the invention
The present invention is directed to overcome the high-heat-conductive composite material of completion method preparation in the prior art easy to reunite and interface compatibility
Loading caused by difference is low, and then the technical issues of influence heating conduction and service performance, provides a kind of new spatial optics knot
Structure high thermal conductivity coefficient cyanate base carbon fiber composite material and preparation method thereof.
To achieve the above object, the invention adopts the following technical scheme:
On the one hand, the present invention provides a kind of space optics structure high thermal conductivity coefficient cyanate base carbon fiber composite material,
The composite material includes cyanate/carbon fibre composite main body and high thermal conductivity functional layer, the high thermal conductivity functional layer covering
In the cyanate/carbon fibre composite main body.
In some embodiments, the composite material is by the cyanate/carbon fibre composite main body and the high thermal conductivity
Functional layer is obtained by integrated curing molding.
In some embodiments, the thermal coefficient of the high thermal conductivity functional layer is 0.5W/ (mK)~2W/ (mK).
In some embodiments, the high thermal conductivity functional layer is by one or more layers high thermal conductivity coefficient cyanate/carbon fibre initial rinse
According to certain laying angle, laying obtains material in cyanate/carbon fibre composite main body.
In some embodiments, the reinforcing material of the high thermal conductivity coefficient cyanate/carbon fiber prepreg is that thermal coefficient exists
One of 30W/ (mK)~200W/ (mK) carbon fiber is a variety of.
In some embodiments, the resin matrix of the high thermal conductivity coefficient cyanate/carbon fiber prepreg is evenly dispersed height
The cyanate ester resin of thermal coefficient filler.
In some embodiments, the high thermal conductivity coefficient filler is selected from graphite, aluminium oxide, magnesia, silicon carbide or carbon nanometer
At least one of pipe.
In some embodiments, with the quality of the high thermal conductivity functional layer for 100%, the quality of the high thermal conductivity coefficient filler
It is 30%~50%.
Yet another aspect, the present invention provide a kind of preparation method of above-mentioned composite material, the preparation method include: S1,
By laying angle and sequence, laying cyanate/carbon fiber prepreg on mold obtains cyanate/carbon fibre composite master
Body, in the high thermal conductivity functional layer of the cyanate/carbon fibre composite main body top laying certain angle；S2, entirety
Enter furnace curing mold pressing to form to obtain the composite material.
In some embodiments, the high thermal conductivity functional layer by ultrasonic disperse high thermal conductivity filler cyanate ester resin glue film
The prepreg laying obtained afterwards with carbon fiber sweat connecting is made.
The beneficial effects of the present invention are: high thermal conductivity coefficient composite material of the invention includes that cyanate/carbon fiber is compound
Body of material and high thermal conductivity functional layer, high thermal conductivity filer content is high in high thermal conductivity functional layer, and with cyanate/carbon fiber composite
Expect that the matrix of main body is consistent, interface problem is not present；Composite body can also be by the resin film and carbon fiber of evenly dispersed filler
Dimension sweat connecting obtains, and the filler collective effect with outer functional layer high-content, loading when solving simple completion method is low, leads
Thermal effect is poor, influences the defect of other performances, while finally having excellent heat conductivity effect, also can guarantee that other performances remain unchanged
Well；Composite material of the invention can be used in space optics structure, and the temperature uniformity of sensor etc. can be improved, for improving
The temperature gradient of lower thermal conductivity structural member is significant on space optical remote sensor.
In composite material of the invention, high thermal conductivity layer using prepreg placement process with composite body in conjunction with after, pass through
Integrated curing molding obtains, and different from the technique and equipment requirement of coating process complexity, less step realizes interface integration knot
It closes, simple process is easy to industrialized production.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with specific embodiment, to this
Invention is further elaborated.It should be appreciated that described herein, specific examples are only used to explain the present invention, without structure
At limitation of the present invention.
The present invention provides a kind of high thermal conductivity coefficient cyanate base carbon fiber composite material, and composite material includes cyanate/carbon
Fiber composite body and high thermal conductivity functional layer, high thermal conductivity functional layer are covered in cyanate/carbon fibre composite main body.
Specifically, composite material is obtained with high thermal conductivity functional layer by integrated curing molding by cyanate/carbon fibre composite main body.
The composite material can be used in space optics structure.
Wherein, high thermal conductivity functional layer is by one or more layers high thermal conductivity coefficient cyanate/carbon fiber prepreg according to certain paving
Layer angle laying in cyanate/carbon fibre composite main body obtains.The thermal coefficient of high thermal conductivity functional layer is 0.5W/ (m
K)~2W/ (mK).
High thermal conductivity coefficient cyanate/carbon fiber prepreg reinforcing material is thermal coefficient in 30W/ (mK)~200W/
(mK) one of carbon fiber is a variety of.In specific embodiment, reinforcing material can be that the toray company trade mark is
M60JB[151.47W/(m·K)]、M55JB[155.75W/(m·K)]、M50[96.64W/(m·K)]、M46[84.29W/
(m·K)]、M40JB[68.67W/(m·K)]、M35[83.93W/(m·K)]、T1000G[31.92W/(m·K)]、T800HB
[35.01W/ (mK)] carbon fiber, Mitsubishi's asphaltic base trade mark are K63712-12k [140W/ (mK)], K1352U-2k [140W/
(mK)] carbon fiber etc..
High thermal conductivity coefficient cyanate/carbon fiber prepreg resin matrix is the cyanic acid of evenly dispersed high thermal conductivity coefficient filler
Ester resin.High thermal conductivity coefficient filler is selected from least one of graphite, aluminium oxide, magnesia, silicon carbide or carbon nanotube.Specifically
In embodiment, with the quality of high thermal conductivity functional layer for 100%, the mass content of high thermal conductivity coefficient filler is 30%~50%,
Filler, which can be uniformly dispersed, while the thermal conductivity of reinforcing material surface layer does not reunite, for properties almost free of losses.
In preferred embodiment, while high thermal conductivity functional layer uses high thermal conductivity coefficient filler, cyanate/carbon fiber
High thermal conductivity coefficient filler is equally also added in composite body, the two cooperates, and double action is conducive to preferably guarantee
The high thermal conductivity of high thermal conductivity coefficient cyanate base carbon fiber composite material of the present invention.With cyanate/carbon fibre composite master
The quality of body is 100%, and the mass content of high thermal conductivity coefficient filler is 2%~10% in composite body.
The present invention also provides a kind of preparation method of above-mentioned composite material, preparation method includes: S1, by laying angle and suitable
Sequence, laying cyanate/carbon fiber prepreg on mold, obtains cyanate/carbon fibre composite main body, in cyanate/carbon
The top laying high thermal conductivity functional layer of fiber composite body；S2, entirety enter furnace curing mold pressing and form to obtain composite material.
Specifically, high thermal conductivity functional layer by after the cyanate ester resin glue film of ultrasonic disperse high thermal conductivity filler with carbon fiber sweat connecting
It obtains.
High thermal conductivity coefficient composite material of the invention includes cyanate/carbon fibre composite main body and high thermal conductivity function
Layer, high thermal conductivity coefficient filer content is high in high thermal conductivity functional layer, and with cyanate/carbon fibre composite main body matrix one
It causes, interface problem is not present；Composite body can also be by the resin film and carbon fiber of evenly dispersed filler (2%~10%wt)
Sweat connecting obtains, and the filler collective effect with outer functional layer high-content, loading when solving simple completion method is low, thermally conductive
Effect is poor, influences the defect of other performances；
The carbon fibre composite of high specific strength, high specific stiffness is generallyd use for space optics structure at present.It is domestic normal
The heating conduction of carbon fibre material is poor, and the thermal conductivity of machine direction only has about 2W/ (mK).And it is of the invention compound
Material can be used in space optics structure, and the temperature uniformity of sensor etc. can be improved, thermally conductive using the truss rod prepared by it
Rate is all larger than 10W/ (mK), makes the stable state axial temperature difference of truss rod less than 2 DEG C, for improving low-heat on space optical remote sensor
The temperature gradient of conductance structural member is significant.
In high thermal conductivity coefficient cyanate base carbon fiber composite material of the invention, high thermal conductivity functional layer uses prepreg laying
After technique is in conjunction with composite body, obtained through integrated curing molding, different from the technique and equipment requirement of coating process complexity,
Less step realizes that interface integration combines, and simple process is easy to industrialized production.
It is described in detail below by way of specific embodiment.
Embodiment 1
In the high thermal conductivity coefficient cyanate base carbon fiber composite material of the present embodiment, cyanate/carbon fibre composite master
The structure of body is by cyanate/carbon fiber prepreg according to [0/90]10Laying laying obtains, and high thermal conductivity functional layer is by cyanate/carbon
Fiber prepreg material is according to 02Laying direct laying in composite body obtains；Cyanate/carbon fiber prepreg is using super
Sound instrument will be dispersed in cyanate ester resin during the pre-polymerization of high thermal conductivity coefficient filler, by above-mentioned resin system on film applicator
It is prepared into after resin film and obtains prepreg with M40JB carbon fiber sweat connecting；Wherein, high thermal conductivity coefficient filler is graphite, compound
The mass content of high thermal conductivity coefficient filler is 5% in body of material, and the quality of high thermal conductivity coefficient filler contains in high thermal conductivity functional layer
Amount is 50%.
Cyanate/carbon fibre composite main body and high thermal conductivity functional layer pass through integrated curing molding, obtain final answer
Condensation material, the thermal coefficient of composite material are 11.66W/ (mK), modulus 115MPa, coefficient of thermal expansion αxFor 1.01*10-6/K；
αyFor 1.51*10-6/K。
Embodiment 2
In the high thermal conductivity coefficient cyanate base carbon fiber composite material of the present embodiment, cyanate/carbon fibre composite master
The structure of body is by cyanate carbon fiber prepreg according to [± 15]8Laying laying obtains, and high thermal conductivity functional layer is by cyanate/carbon fiber
Prepreg is tieed up according to 02Laying direct laying in composite body obtains；Cyanate/carbon fiber prepreg is to utilize ultrasound
Instrument will be dispersed in cyanate ester resin during the pre-polymerization of high thermal conductivity coefficient filler, and above-mentioned resin system is made on film applicator
It is standby to obtain prepreg with M55JB carbon fiber sweat connecting at after resin film；Wherein, high thermal conductivity coefficient filler is aluminium oxide, compound
The mass content of high thermal conductivity coefficient filler is 2% in body of material, and the quality of high thermal conductivity coefficient filler contains in high thermal conductivity functional layer
Amount is 50%.
Cyanate/carbon fibre composite main body and high thermal conductivity functional layer pass through integrated curing molding, obtain final answer
Condensation material, the thermal coefficient of composite material are 11.45W/ (mK), modulus 213MPa, coefficient of thermal expansion αxFor -1.83*10-6/
K；αyFor 17.8*10-6/ K, bending strength change rate is -7.9% to ultraviolet irradiation (absorbed dose 2000ESH) afterwards, bending modulus
Change rate is 5.7%, and interlaminar shear strength change rate is -16.5%, and mass loss rate is -0.25%.
Embodiment 3
In the high thermal conductivity coefficient cyanate base carbon fiber composite material of the present embodiment, cyanate/carbon fibre composite master
The structure of body is by cyanate/carbon fiber prepreg according to [0/90/ ± 45]8Laying laying obtains, and high thermal conductivity functional layer is by cyanic acid
Ester/carbon fiber prepreg is according to ± 152Laying direct laying in composite body obtains；Cyanate/carbon fiber prepreg
It is that will be dispersed in cyanate ester resin during the pre-polymerization of high thermal conductivity coefficient filler using Ultrasound Instrument, above-mentioned resin system is existed
It is prepared on film applicator after resin film and obtains prepreg with M55JB carbon fiber sweat connecting；Wherein, high thermal conductivity coefficient filler is oxygen
Change aluminium and magnesia, the mass content of high thermal conductivity coefficient filler is 2% in composite body, high thermal conductivity in high thermal conductivity functional layer
The mass content of coefficient filler is 40%.
Cyanate/carbon fibre composite main body and high thermal conductivity functional layer pass through integrated curing molding, obtain final answer
Condensation material, the thermal coefficient of composite material are 16.95W/ (mK), modulus 112MPa, coefficient of thermal expansion αxFor 0.222*10-6/
K；αyFor 0.609*10-6/K。
Embodiment 4
In the high thermal conductivity coefficient cyanate base carbon fiber composite material of the present embodiment, cyanate/carbon fibre composite master
The structure of body is by cyanate/carbon fiber prepreg according to [0/ ± 60]10Laying laying obtains, high thermal conductivity functional layer by cyanate/
Carbon fiber prepreg is according to ± 302Laying direct laying in composite body obtains；Cyanate/carbon fiber prepreg is benefit
It will be dispersed in cyanate ester resin during the pre-polymerization of high thermal conductivity coefficient filler with Ultrasound Instrument, by above-mentioned resin system in film
It is prepared on machine after resin film and obtains prepreg with M55JB carbon fiber sweat connecting, wherein high thermal conductivity coefficient filler is carbon nanometer
It manages, the mass content of high thermal conductivity coefficient filler is 3% in composite body, high thermal conductivity coefficient filler in high thermal conductivity functional layer
Mass content is 45%.
Cyanate/carbon fibre composite main body and high thermal conductivity functional layer pass through integrated curing molding, obtain final answer
Condensation material, the thermal coefficient of composite material are 10.47W/ (mK), modulus 106MPa, coefficient of thermal expansion αxFor 0.253*10-6/K；
αyFor 0.552*10-6/ K, and under vacuum condition (125 DEG C, 1*10-3Pa) total matter damage TML is 0.177%, can coagulate volatile content
CVCM0.005%, water vapour resorption amount WVR0.124%.
Embodiment 5
In the high thermal conductivity coefficient cyanate base carbon fiber composite material of the present embodiment, cyanate/carbon fibre composite master
The structure of body is by cyanate/carbon fiber prepreg according to [0/90/ ± 45]8Laying laying obtains, and high thermal conductivity functional layer is by cyanic acid
Ester/carbon fiber prepreg is according to 02Laying direct laying in composite body obtains；Cyanate/carbon fiber prepreg is benefit
It will be dispersed in cyanate ester resin during the pre-polymerization of high thermal conductivity coefficient filler with Ultrasound Instrument, by above-mentioned resin system in film
It is prepared on machine after resin film and obtains prepreg with T800HB or M55JB carbon fiber sweat connecting；Wherein, in composite body
The carbon fiber used is T800HB, and the carbon fiber that high thermal conductivity functional layer uses is M55JB；High thermal conductivity coefficient filler is silicon carbide,
The mass content of high thermal conductivity coefficient filler is 10% in composite body, the matter of high thermal conductivity coefficient filler in high thermal conductivity functional layer
Measuring content is 50%.
Cyanate/carbon fibre composite main body and high thermal conductivity functional layer pass through integrated curing molding, obtain final answer
Condensation material, the thermal coefficient of composite material are 10.36W/ (mK), modulus 74MPa, coefficient of thermal expansion αxFor 1.32*10-6/K；
αyFor 2.23*10-6/K。
To sum up, high thermal conductivity coefficient cyanate base carbon fiber composite material of the invention, by the tree of evenly dispersed filler
Adipose membrane and carbon fiber sweat connecting obtain composite body, the filler collective effect with high thermal conductivity functional layer high-content, solve
Loading when simple completion method is low, and heat-conducting effect is poor, influences the defect of other performances, having the same of excellent heat conductivity effect
When, it also can guarantee that other performances are still good.
High thermal conductivity coefficient cyanate base carbon fiber composite material of the invention can be used in space optics structure, can be improved quick
The temperature uniformity of sensor etc. is all larger than 10W/ (mK) using the truss rod thermal conductivity prepared by it, makes the stable state of truss rod
Axial temperature difference is significant for the temperature gradient for improving lower thermal conductivity structural member on space optical remote sensor less than 2 DEG C.
The above described specific embodiments of the present invention are not intended to limit the scope of the present invention..Any basis
Any other various changes and modifications made by technical concept of the invention should be included in the guarantor of the claims in the present invention
It protects in range.
Claims (10)
1. a kind of high thermal conductivity coefficient cyanate base carbon fiber composite material, which is characterized in that the composite material is by cyanate/carbon
Fiber composite body and high thermal conductivity functional layer composition, it is multiple that the high thermal conductivity functional layer is covered on the cyanate/carbon fiber
In condensation material main body.
2. composite material as described in claim 1, which is characterized in that the composite material is multiple by the cyanate/carbon fiber
Condensation material main body is obtained with the high thermal conductivity functional layer by integrated curing molding.
3. composite material as described in claim 1, which is characterized in that the thermal coefficient of the high thermal conductivity functional layer is 0.5W/
(mK)~2W/ (mK).
4. composite material as described in claim 1, which is characterized in that the high thermal conductivity functional layer is by one or more layers high thermal conductivity
According to certain laying angle, the laying in cyanate/carbon fibre composite main body obtains coefficient cyanate/carbon fiber prepreg.
5. composite material as claimed in claim 4, which is characterized in that the high thermal conductivity coefficient cyanate/carbon fiber prepreg
Reinforcing material be thermal coefficient in one of 30W/ (mK)~200W/ (mK) carbon fiber or a variety of.
6. composite material as claimed in claim 4, which is characterized in that the high thermal conductivity coefficient cyanate/carbon fiber prepreg
Resin matrix be evenly dispersed high thermal conductivity coefficient filler cyanate ester resin.
7. composite material as claimed in claim 6, which is characterized in that the high thermal conductivity coefficient filler be selected from graphite, aluminium oxide,
At least one of magnesia, silicon carbide or carbon nanotube.
8. composite material as claimed in claim 7, which is characterized in that with the quality of the high thermal conductivity functional layer for 100%, institute
The quality for stating high thermal conductivity coefficient filler is 30%~50%.
9. a kind of preparation method of composite material as described in claim 1, which is characterized in that the preparation method includes:
S1, laying angle and sequence are pressed, laying cyanate/carbon fiber prepreg, it is compound to obtain cyanate/carbon fiber on mold
Body of material, in the cyanate/carbon fibre composite main body top laying high thermal conductivity functional layer；
S2, entirety enter furnace curing mold pressing and form to obtain the composite material.
10. a kind of preparation method as claimed in claim 9, which is characterized in that the high thermal conductivity functional layer is by ultrasonic disperse height
The prepreg laying obtained after the cyanate ester resin glue film of heat filling with carbon fiber sweat connecting is made.
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| CN109796759B (en) | 2021-12-24 |
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