CN109988395B - Epoxy resin-glass fiber prepreg, resin fiber composite material, preparation method of resin fiber composite material and aviation aircraft - Google Patents
Epoxy resin-glass fiber prepreg, resin fiber composite material, preparation method of resin fiber composite material and aviation aircraft Download PDFInfo
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Abstract
The invention provides an epoxy resin-glass fiber prepreg, a resin fiber composite material, a preparation method thereof and an aviation aircraft. The epoxy resin content in the epoxy resin-glass fiber prepreg is 45-60 wt%. The improved epoxy-glass fiber prepregs of the present application contain a relatively high level of epoxy resin. By increasing the content of the epoxy resin, the infiltration area between the glass fiber and the epoxy resin can be increased, the content of residual air in the composite material is reduced, the porosity of the prepared composite material is reduced, the puncture resistance of the composite material is further improved, and the insulating property of the composite material is improved.
Description
Technical Field
The invention relates to the field of composite materials, in particular to an epoxy resin-glass fiber prepreg, a resin fiber composite material, a preparation method of the epoxy resin-glass fiber prepreg and the resin fiber composite material, and an aviation aircraft.
Background
At present, the method for improving the insulating property of the composite material changes the type and the proportion of an epoxy resin curing agent, and improves the insulating property of the composite material by modifying a resin matrix.
Due to the need of modifying the resin system, the development period is long, the cost is high, and the application of the composite material is greatly limited.
Disclosure of Invention
The invention mainly aims to provide an epoxy resin-glass fiber prepreg, a resin fiber composite material, a preparation method thereof and an aviation aircraft, so as to solve the problem that the resin fiber composite material in the prior art is poor in insulating property.
In order to achieve the above object, according to one aspect of the present invention, there is provided an epoxy resin-glass fiber prepreg having an epoxy resin content of 45 to 60 wt%.
In order to achieve the above object, according to a second aspect of the present invention, there is provided a resin fiber composite material, including an epoxy resin-glass fiber cured film layer, wherein the epoxy resin content in the epoxy resin-glass fiber cured film layer is 45 to 60 wt%.
According to a third aspect of the present invention, there is provided a method for producing the above resin fiber composite material, the method comprising: setting an epoxy resin-glass fiber layer to be cured, wherein the epoxy resin content is 45-60 wt%; arranging an exhaust isolation layer on the epoxy resin-glass fiber layer to be cured to form a body to be cured; and curing the body to be cured to obtain the resin fiber composite material.
Further, the step of arranging the epoxy resin-glass fiber layer to be cured with the epoxy resin content of 45-60 wt% comprises the following steps: the epoxy resin-glass fiber prepreg with the epoxy resin content of 45-60 wt% is used for manufacturing the epoxy resin-glass fiber to-be-cured layer.
Further, the step of arranging the epoxy resin-glass fiber layer to be cured with the epoxy resin content of 45-60 wt% comprises the following steps: laminating an epoxy resin-glass fiber prepreg with the epoxy resin content of 30-40 wt% and an epoxy resin adhesive film to obtain an epoxy resin-glass fiber to-be-cured layer with the epoxy resin content of 45-60 wt%, wherein the epoxy resin in the epoxy resin adhesive film layer is the same as the epoxy resin in the epoxy resin-glass fiber prepreg.
Furthermore, every 2-4 layers of epoxy resin-glass fiber prepreg and one layer of epoxy resin adhesive film are arranged in a laminated mode.
Further, the epoxy resin film layer is set to be 3-7 layers.
Further, the thickness of each epoxy resin film layer is 0.1 +/-0.01 mm.
Further, the step of paving an exhaust isolation layer on the epoxy resin-glass fiber layer to be cured to form the body to be cured comprises the following steps: and sequentially paving demoulding cloth, an isolating membrane and an air-permeable felt on the epoxy resin-glass fiber layer to be cured to form a body to be cured.
According to a fourth aspect of the present invention, there is provided an aircraft comprising a resin fiber composite material, wherein the resin fiber composite material is the resin fiber composite material or the resin fiber composite material prepared by any one of the above preparation methods.
Compared with the conventional epoxy resin-glass fiber prepreg with the content of 30-40 wt%, the epoxy resin-glass fiber prepreg improved by the method provided by the invention contains epoxy resin with higher content. By increasing the content of the epoxy resin, the infiltration area between the glass fiber and the epoxy resin can be increased, the content of residual air in the composite material is reduced, the porosity of the prepared composite material is reduced, the puncture resistance of the composite material is further improved, and the insulating property of the composite material is improved.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail with reference to examples.
Prepreg preparation: the composition of the resin matrix and reinforcement, which is made by impregnating continuous fibers or fabrics with the resin matrix under strictly controlled conditions, is an intermediate material in the manufacture of composites.
Classification of prepregs:
1) the prepreg is classified into a thermosetting resin prepreg and a thermoplastic resin prepreg according to the resin matrix.
2) The prepreg is classified into a carbon fiber (fabric) prepreg, a glass fiber (fabric) prepreg, and an aramid fiber (fabric) prepreg according to the difference of the reinforcing material.
3) According to the different curing temperatures, the prepreg can be divided into a medium-temperature curing (120 ℃) prepreg, a high-temperature curing (120 ℃) prepreg and a prepreg with the curing temperature exceeding 200 ℃.
Prepregs of the usual specifications have, in terms of fiber content per unit area: c020, C030, C050, C075, C100, C125, C150, C175, C200, and the like, in terms of resin content, and are divided into 25%, 33%, 37%, 40%, and the like.
As mentioned in the background art, the existing resin fiber composite materials have the defect of poor insulation performance, and the existing schemes for improving the insulation performance of the composite materials are realized by modifying resin, but the development period of the schemes is long and the cost is high. Thus, in order to improve the defect of poor insulation performance, the present application proposes a new solution from a completely different idea from the prior art. In one exemplary embodiment of the present application, an epoxy-glass fiber prepreg is provided, wherein the epoxy resin content in the epoxy-glass fiber prepreg is 45 to 60 wt%.
Compared with the existing epoxy resin-glass fiber prepreg with the content of 30-40 wt%, the epoxy resin-glass fiber prepreg improved by the application contains epoxy resin with higher content. By improving the content of the epoxy resin, the infiltration area between the glass fiber and the epoxy resin can be increased, the probability of air existence is reduced, the porosity of the prepared composite material is reduced, and the breakdown strength of the composite material is further improved, namely the insulating property of the composite material is improved.
In a second exemplary embodiment of the present application, a resin fiber composite material is further provided, where the resin fiber composite material includes an epoxy resin-glass fiber cured film layer, and a content of the epoxy resin in the epoxy resin-glass fiber cured film layer is 45 to 60 wt%.
The improved resin fiber composite material has the advantages that the content of epoxy resin in the epoxy resin-glass fiber curing film layer is 45-60 wt%, and is higher than that of epoxy resin in the existing epoxy resin-glass fiber curing film layer (by 30-40 wt%), so that the infiltration effect between the glass fiber and the epoxy resin can be increased in the flowing stage of the epoxy resin in the curing process, the air residue inside a composite material part is reduced, the porosity of the composite material is reduced, the insulating property of the composite material is enhanced, and the breakdown strength is improved.
In a third exemplary embodiment of the present application, there is also provided a method of preparing a resin fiber composite material, the method including: setting an epoxy resin-glass fiber layer to be cured, wherein the epoxy resin content is 45-60 wt%; paving an exhaust isolation layer on the epoxy resin-glass fiber layer to be cured to form a body to be cured; and curing the body to be cured to obtain the resin fiber composite material.
According to the preparation method of the resin fiber composite material, the epoxy resin-glass fiber to-be-cured layer with the increased epoxy resin content is arranged, so that the resin content in the pre-cured body is increased, the flowability of the epoxy resin in the curing process is increased, the infiltration effect between the glass fiber and the epoxy resin is further increased, the air residue in the composite material part is reduced, the porosity of the composite material is reduced, the insulating property of the composite material is enhanced, and the anti-breakdown strength is improved.
In the above preparation method, the step of providing the epoxy resin-glass fiber layer to be cured having an epoxy resin content of 45 to 60 wt% is not particularly limited as long as the epoxy resin content in the layer to be cured is formed within a range of 45 to 60 wt%. In a preferred embodiment of the present application, the step of providing the epoxy resin-glass fiber layer to be cured with an epoxy resin content of 45-60 wt% directly uses an epoxy resin-glass fiber prepreg with an epoxy resin content of 45-60 wt% to make the epoxy resin-glass fiber layer to be cured.
In the preferred embodiment, the content of the epoxy resin in the existing epoxy resin-glass fiber prepreg is directly increased to 45-60 wt%, so that the prepreg with high epoxy resin content is formed. In the curing process of the layer to be cured, the epoxy resin has better flow uniformity, so that the obtained composite material has lower porosity, higher compactness, better insulating property and breakdown strength, and the whole preparation process is relatively simple and convenient to operate.
In another preferred embodiment of the present application, the step of providing the epoxy resin-glass fiber layer to be cured with an epoxy resin content of 45 to 60 wt% comprises: laminating an epoxy resin-glass fiber prepreg with the epoxy resin content of 30-40 wt% and an epoxy resin adhesive film to obtain an epoxy resin-glass fiber to-be-cured layer with the epoxy resin content of 45-60 wt%, wherein the epoxy resin in the epoxy resin adhesive film layer is the same as the epoxy resin in the epoxy resin-glass fiber prepreg.
In the preferred embodiment, the epoxy resin-glass fiber prepreg paving layer with the resin content of 30-40 wt% and the epoxy resin adhesive film layer are stacked, and the epoxy resin in the epoxy resin adhesive film layer is the same as the epoxy resin in the prepreg, so that the flowability of the epoxy resin in the curing process is increased, the infiltration effect between the glass fiber and the epoxy resin is further increased, the air residue in the composite material part is reduced, the porosity of the composite material is reduced, the insulating property of the composite material is enhanced, and the breakdown strength is improved.
Specifically, the specific arrangement manner of the lamination arrangement of the epoxy resin-glass fiber prepreg layup layer and the epoxy resin glue film layer of 30-40 wt% is not particularly limited, as long as the content of the epoxy resin in the finally obtained layer to be cured is within the range of 45-60 wt%.
In a preferred embodiment of the present application, every 2-4 layers of epoxy resin-glass fiber prepregs are stacked with one layer of epoxy resin adhesive film. The arrangement mode is beneficial to improving the wetting effect of the epoxy resin on the glass fiber.
In another preferred embodiment of the present application, the epoxy resin adhesive film layer is provided with 3 to 7 layers; more preferably, the thickness of each epoxy resin film layer is 0.1 +/-0.01 mm.
The resin adhesive film layers are arranged to be 3-7 layers, so that the process is easy to implement, and the soaking effect of the glass fibers in the epoxy resin is better. The thickness of each epoxy resin adhesive film layer is set to be about 0.1mm, so that the epoxy resin adhesive films can more easily soak glass fibers in adjacent prepreg layers in the curing process, and the glass fiber soaking effect is better.
In another preferred embodiment of the present application, the step of laying an exhaust isolation layer on the epoxy resin-glass fiber layer to be cured to form the body to be cured includes: and sequentially paving demoulding cloth, an isolating membrane and an air-permeable felt on the epoxy resin-glass fiber layer to be cured to form a body to be cured.
In the preparation method of the resin fiber composite material, the exhaust isolation layer is an auxiliary film layer in the preparation process and plays a role in exhausting in the curing process. The specific material of the exhaust isolation layer is the exhaust isolation layer made of the conventional composite material, and the material specifically used by each layer can be reasonably selected according to actual needs. In a preferred embodiment, the exhaust isolation layer includes a release fabric layer, an isolation film layer and an air-permeable felt layer, which are sequentially disposed on the epoxy resin-glass fiber layer to be cured. In another preferred embodiment of the present application, the release fabric is a teflon release fabric, which has a smooth surface, is not easily bonded to the adhesive layer, and is easier to release. The isolating film is used for isolating the lower film layer from the upper film layer so as to prevent the vacuum bag which plays a protective role from being damaged. Preferably, a non-porous isolating membrane is adopted, and the non-porous isolating membrane can completely isolate the lower membrane layer from permeating into the upper membrane layer, so that a good protection effect is achieved.
According to a fourth aspect of the present invention, there is provided an aircraft comprising a resin fiber composite material, wherein the resin fiber composite material is the resin fiber composite material or the resin fiber composite material prepared by any one of the above preparation methods. The aviation aircraft prepared from the resin fiber composite material has the effect of excellent insulating property.
The advantageous effects of the present application will be further described with reference to specific examples.
Example 1
Paving and pasting 36 wt% epoxy resin-quartz fiber prepreg, paving and pasting 3 layers of prepreg every time, paving and pasting a layer of epoxy resin adhesive film with the thickness of 0.1mm, preparing a vacuum bag, pre-compacting at normal temperature for 15-30 mins, paving and pasting 3 layers of adhesive films together to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 70KV/mm, and compared with the epoxy resin-quartz fiber composite material without an adhesive film, the insulation strength of the sample is improved by 40 KV/mm.
Example 2
Paving and pasting 30 wt% epoxy resin-quartz fiber prepreg, paving and pasting 2 layers of prepreg every time, paving and pasting a layer of epoxy resin adhesive film with the thickness of 0.09mm, preparing a vacuum bag, pre-compacting at normal temperature for 15-30 mins, paving and pasting 7 layers of adhesive films together to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 67KV/mm, and the insulation strength is improved by 30KV/mm compared with the epoxy resin-quartz fiber composite material without an adhesive film.
Example 3
Paving and pasting 40 wt% epoxy resin-quartz fiber prepreg, paving and pasting 4 layers of prepreg every time, paving and pasting a layer of epoxy resin adhesive film with the thickness of 0.11mm, preparing a vacuum bag, pre-compacting at normal temperature for 15-30 mins, paving and pasting 2 layers of adhesive films together to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 68KV/mm, and compared with the epoxy resin-quartz fiber composite material without an adhesive film, the insulation strength of the sample is improved by 41 KV/mm.
Example 4
Paving and pasting 45 wt% epoxy resin-quartz fiber prepreg, preparing a vacuum bag after 3 layers of prepreg are paved and pasted in the paving and pasting process, and pre-compacting at normal temperature for 15-30 mins to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 90KV/mm, and is improved by 60KV/mm compared with a prepreg composite material with low epoxy resin content (30-40%).
Example 5
Paving and pasting 50 wt% epoxy resin-quartz fiber prepreg, preparing a vacuum bag after 3 layers of prepreg are paved and pasted in the paving and pasting process, and pre-compacting at normal temperature for 15-30 mins to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 100KV/mm, and is improved by 65KV/mm compared with a prepreg composite material with low epoxy resin content (30-40%).
Example 6
Paving and pasting the epoxy resin-quartz fiber prepreg with the content of 55 wt%, preparing a vacuum bag after 3 layers of prepreg are paved and pasted in the paving and pasting process, and pre-compacting at normal temperature for 15-30 mins to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 91KV/mm, and is improved by 60KV/mm compared with a prepreg composite material with low epoxy resin content (30-40%).
Example 7
Paving and pasting epoxy resin-quartz fiber prepreg with the content of 60 wt%, preparing a vacuum bag after 3 layers of prepreg are paved and pasted in the paving and pasting process, and pre-compacting at normal temperature for 15-30 mins to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 90KV/mm, and is improved by 59KV/mm compared with a prepreg composite material with low epoxy resin content (30-40%).
Comparative example 1
Paving and pasting 70 wt% epoxy resin-quartz fiber prepreg, preparing a vacuum bag after 3 layers of prepreg are paved and pasted in the paving and pasting process, and pre-compacting at normal temperature for 15-30 mins to form an epoxy resin-quartz fiber to-be-cured layer;
then sequentially paving polytetrafluoroethylene demolding cloth, a non-porous isolating film, a breathable felt and a vacuum bag film on the surface of the epoxy resin-quartz fiber layer to be cured, vacuumizing and pre-compacting for 30mins at normal temperature to form a body to be cured;
putting a body to be cured into an autoclave, and curing according to the following curing procedure: heating from normal temperature to 90 deg.C for 0.5 hr, curing at the temperature for 1 hr, then heating to 140 deg.C for 0.5 hr, and curing at the temperature for 4 hr, wherein the pressure in autoclave is maintained at 0.3 MPa. After the solidification is finished, the temperature is reduced to 60 ℃ at a cooling speed of not more than 2 ℃/min, and then the autoclave is opened to obtain the resin fiber composite material.
And finally, measuring the breakdown voltage of the resin fiber composite material sample under the action of the vertical breakdown electrode by using a voltage breakdown tester to determine the insulation strength.
The test result shows that the breakdown voltage of the sample can reach 45KV/mm, and the sample has no obvious difference compared with the prepreg composite material with low epoxy resin content (30-40%).
From the above description, it can be seen that the above-described embodiments of the present application achieve the following technical effects: on the premise of not modifying the original epoxy resin, the content of the epoxy resin in the prepreg is increased, or the content of the epoxy resin is increased in the step of forming the epoxy resin-glass fiber to-be-cured layer, so that the infiltration area between the glass fiber and the glass fiber resin can be increased, the air residual quantity in the composite material is reduced, the porosity of the composite material is reduced, and the breakdown strength of the composite material is further improved. The composite material prepared by the method is excellent in insulativity, greatly shortens the research and development period and the development cost, and can be rapidly applied.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The preparation method of the resin fiber composite material is characterized in that the resin fiber composite material comprises an epoxy resin-glass fiber curing film layer, wherein the epoxy resin content in the epoxy resin-glass fiber curing film layer is 45-60 wt%; the epoxy resin is unmodified epoxy resin; the preparation method comprises the following steps:
setting an epoxy resin-glass fiber layer to be cured, wherein the epoxy resin content is 45-60 wt%;
arranging an exhaust isolation layer on the epoxy resin-glass fiber layer to be cured to form a body to be cured; and
curing the body to be cured to obtain the resin fiber composite material;
when the content of the epoxy resin in the epoxy resin-glass fiber prepreg is 45-60 wt%, the step of setting the epoxy resin-glass fiber layer to be cured, the epoxy resin content of which is 45-60 wt%, includes:
preparing the epoxy resin-glass fiber to-be-cured layer by using an epoxy resin-glass fiber prepreg with the epoxy resin content of 45-60 wt%;
when the content of the epoxy resin in the epoxy resin-glass fiber prepreg is 30-40 wt%, the step of setting the epoxy resin-glass fiber layer to be cured, the content of the epoxy resin being 45-60 wt%, includes:
laminating an epoxy resin-glass fiber prepreg with the epoxy resin content of 30-40 wt% and an epoxy resin adhesive film to obtain an epoxy resin-glass fiber to-be-cured layer with the epoxy resin content of 45-60 wt%, wherein the epoxy resin in the epoxy resin adhesive film layer is the same as the epoxy resin in the epoxy resin-glass fiber prepreg;
wherein the breakdown voltage of the resin fiber composite material prepared when the content of the epoxy resin in the epoxy resin-glass fiber prepreg is 45-60 wt% is higher than the breakdown voltage of the resin fiber composite material prepared when the content of the epoxy resin in the epoxy resin-glass fiber prepreg is 30-40 wt%.
2. The preparation method according to claim 1, wherein every 2-4 layers of the epoxy resin-glass fiber prepreg and one layer of the epoxy resin adhesive film are stacked.
3. The method according to claim 2, wherein the epoxy resin adhesive film layer is provided in 3 to 7 layers.
4. The method according to claim 2, wherein the thickness of each of the epoxy resin adhesive film layers is 0.1 ± 0.01 mm.
5. The manufacturing method according to claim 1, wherein the step of laying an exhaust isolation layer on the epoxy resin-glass fiber layer to be cured to form a body to be cured comprises:
and sequentially paving demolding cloth, an isolating film and an air felt on the epoxy resin-glass fiber layer to be cured to form the body to be cured.
6. The production method according to claim 5,
the demolding cloth is polytetrafluoroethylene demolding cloth, and the isolating membrane is a nonporous isolating membrane.
7. An aircraft comprising a resin fiber composite material, wherein the resin fiber composite material is the resin fiber composite material produced by the production method according to any one of claims 1 to 6.
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202271590U (en) * | 2011-09-07 | 2012-06-13 | 浙江华正新材料股份有限公司 | CEM-1 copper clad plate made of resin matrix composite materials |
| CN102837429A (en) * | 2012-09-07 | 2012-12-26 | 中国航空工业集团公司北京航空材料研究院 | Orientated non-continuous fiber prepreg and preparation equipment thereof |
| CN103895315A (en) * | 2014-02-19 | 2014-07-02 | 南京航空航天大学 | Preparation molding method of Glare component |
| WO2014147222A2 (en) * | 2013-03-22 | 2014-09-25 | Hexcel Holding Gmbh | Improvements in or relating to fibre reinforced composites |
| CN104441693A (en) * | 2014-12-05 | 2015-03-25 | 苗宏伟 | Molding process method for novel composite material adhesive film of wind power generation blades |
| CN104842619A (en) * | 2015-05-06 | 2015-08-19 | 江苏恒神股份有限公司 | Prepreg manufacturing process of high-tenacity multilayer structure |
| CN105856588A (en) * | 2015-12-25 | 2016-08-17 | 广东生益科技股份有限公司 | Insulating board and insulating glue sheet for laminated busbar, and production methods thereof |
| CN106042528A (en) * | 2016-05-31 | 2016-10-26 | 中国科学院理化技术研究所 | Novel low-temperature insulation and thermal insulation pre-impregnated fiber cloth and preparation method thereof |
| CN106584882A (en) * | 2016-11-29 | 2017-04-26 | 中广核俊尔新材料有限公司 | High-speed motor car equipment compartment beam made of carbon fiber composite and manufacturing method of high-speed motor car equipment compartment beam |
| CN106739043A (en) * | 2017-03-17 | 2017-05-31 | 零八电子集团四川天源机械有限公司 | PMI foam layers radome of fighter and its manufacture method |
| CN107187020A (en) * | 2017-06-06 | 2017-09-22 | 中国电子科技集团公司第三十八研究所 | A kind of fibre reinforced composites 3D printing assistant formation method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9532466B2 (en) * | 2011-12-22 | 2016-12-27 | Haesung Ds Co., Ltd. | Method of manufacturing multi-layer circuit board and multi-layer circuit board manufactured by using the method |
-
2017
- 2017-12-29 CN CN201711489869.7A patent/CN109988395B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202271590U (en) * | 2011-09-07 | 2012-06-13 | 浙江华正新材料股份有限公司 | CEM-1 copper clad plate made of resin matrix composite materials |
| CN102837429A (en) * | 2012-09-07 | 2012-12-26 | 中国航空工业集团公司北京航空材料研究院 | Orientated non-continuous fiber prepreg and preparation equipment thereof |
| WO2014147222A2 (en) * | 2013-03-22 | 2014-09-25 | Hexcel Holding Gmbh | Improvements in or relating to fibre reinforced composites |
| CN103895315A (en) * | 2014-02-19 | 2014-07-02 | 南京航空航天大学 | Preparation molding method of Glare component |
| CN104441693A (en) * | 2014-12-05 | 2015-03-25 | 苗宏伟 | Molding process method for novel composite material adhesive film of wind power generation blades |
| CN104842619A (en) * | 2015-05-06 | 2015-08-19 | 江苏恒神股份有限公司 | Prepreg manufacturing process of high-tenacity multilayer structure |
| CN105856588A (en) * | 2015-12-25 | 2016-08-17 | 广东生益科技股份有限公司 | Insulating board and insulating glue sheet for laminated busbar, and production methods thereof |
| CN106042528A (en) * | 2016-05-31 | 2016-10-26 | 中国科学院理化技术研究所 | Novel low-temperature insulation and thermal insulation pre-impregnated fiber cloth and preparation method thereof |
| CN106584882A (en) * | 2016-11-29 | 2017-04-26 | 中广核俊尔新材料有限公司 | High-speed motor car equipment compartment beam made of carbon fiber composite and manufacturing method of high-speed motor car equipment compartment beam |
| CN106739043A (en) * | 2017-03-17 | 2017-05-31 | 零八电子集团四川天源机械有限公司 | PMI foam layers radome of fighter and its manufacture method |
| CN107187020A (en) * | 2017-06-06 | 2017-09-22 | 中国电子科技集团公司第三十八研究所 | A kind of fibre reinforced composites 3D printing assistant formation method |
Non-Patent Citations (1)
| Title |
|---|
| 高压固体复合绝缘材料电击穿试验研究;敖明 等;《高电压技术》;19990331;第25卷(第1期);第21-22、25页 * |
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