CN108839359B - Composite material member curing process and composite material part - Google Patents
Composite material member curing process and composite material part Download PDFInfo
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- CN108839359B CN108839359B CN201810639024.XA CN201810639024A CN108839359B CN 108839359 B CN108839359 B CN 108839359B CN 201810639024 A CN201810639024 A CN 201810639024A CN 108839359 B CN108839359 B CN 108839359B
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
Abstract
The invention belongs to the field of materials, and relates to a composite material member curing process and a composite material part, wherein the curing process comprises the following steps: 1) heating and insulating the composite material workpiece to be processed in a vibration experiment platform; 2) in the heating and heat preservation processes, vibrating the composite material workpiece to be processed through a vibration experiment platform; 3) after the vibration is finished, applying low pressure to the composite material workpiece to be processed through a vibration experiment platform; 4) and in the process of applying the low pressure, carrying out secondary temperature rise on the composite material workpiece to be processed and finishing the subsequent curing of the composite material workpiece to be processed. The invention provides a composite material part curing process which can obviously reduce the porosity of a composite material part under low curing pressure, improve the performance of the composite material part and realize safe, efficient and energy-saving forming and curing of a large composite material part.
Description
Technical Field
The invention belongs to the field of materials, relates to a composite material member curing process and a composite material part, and particularly relates to a composite material member curing process under vibration pretreatment and low-pressure environment and a composite material part prepared based on the curing process.
Background
The composite material part is widely applied to high and new fields such as aerospace and the like due to a plurality of advantages, but the safety and the reliability of the composite material part in practical engineering can be seriously influenced due to the existence of pores. Thus, aeronautical standards require porosity within composite parts of less than 1%, and other industries require porosity of less than 5%. At present, the way of reducing the porosity of the composite material part is mainly to use the autoclave high-pressure process to finish the molding of the composite material part with low porosity in a high-pressure environment. However, the process still has the engineering practical problems of high manufacturing cost, dangerous use, high energy consumption, high curing pressure and uniformity requirements, large molding manufacturing difficulty and the like.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a composite material part curing process which can obviously reduce the porosity of a composite material part under low curing pressure, improve the performance of the composite material part and realize safe, efficient and energy-saving forming and curing of a large composite material part.
In order to achieve the purpose, the invention adopts the following technical scheme:
a composite material member curing process is characterized in that: the composite material member curing process comprises the following steps:
1) heating and insulating the composite material workpiece to be processed in a vibration experiment platform;
2) in the heating and heat preservation processes, vibration is provided for the composite material workpiece to be processed through a vibration experiment platform;
3) after the vibration is finished, applying low pressure to the composite material workpiece to be processed through a vibration experiment platform;
4) and in the process of applying the low pressure, carrying out secondary temperature rise on the composite material workpiece to be processed and finishing the subsequent curing of the composite material workpiece to be processed.
Preferably, the specific implementation manner of the heating and heat preservation treatment in the step 1) adopted by the invention is as follows: heating the composite material workpiece to be processed from 30 ℃ to 80 ℃ in a vibration experiment platform, and preserving heat for 30 min.
Preferably, the composite material part to be processed in step 1) adopted by the invention is heated from 30 ℃ to 80 ℃ in a vibration experiment platform at a heating rate of 1.5 ℃/min.
Preferably, the vibration in step 2) employed in the present invention is 5g to 20g, and g is 9.8 m/s.
Preferably, the low pressure in step 3) employed in the present invention is 0MPa to 0.2 MPa.
Preferably, the secondary heating in the step 4) adopted by the invention is to heat the composite material workpiece to be processed from 80 ℃ to 180 ℃, and the temperature is kept for 120 min.
Preferably, the second temperature rise in step 4) adopted in the invention is to heat the composite material part to be processed from 80 degrees to 180 degrees at a temperature rise rate of 1.5 ℃/min.
Preferably, the heating, heat preservation and secondary temperature rise adopted by the invention are performed by a nichrome heating wire heater.
Preferably, the vibration frequency range of the vibration experiment platform adopted by the invention is 10HZ-2000 HZ; the temperature range of the vibration experiment platform is-70-200 ℃; the vibration acceleration of the vibration test platform is not more than 50g, and g is 9.8 m/s.
A composite part is prepared based on the composite member curing process as described above.
The invention has the advantages that:
the invention provides a composite material member curing process and a composite material part, and the method comprises the steps of 1) heating and heat preservation treatment of the composite material part to be processed in a vibration experiment platform; 2) in the heating and heat preservation processes, vibrating the composite material workpiece to be processed through a vibration experiment platform; 3) after the vibration is finished, applying low pressure to the composite material workpiece to be processed through a vibration experiment platform; 4) and in the process of applying the low pressure, carrying out secondary temperature rise on the composite material workpiece to be processed and finishing the subsequent curing of the composite material workpiece to be processed. The invention provides a novel molding process of vibration pretreatment and low-pressure curing of a composite material part, aiming at the problem of high molding and manufacturing difficulty caused by high requirements of high-performance large-scale composite material parts on curing pressure and uniformity thereof. In terms of porosity, after the composite material product is subjected to random vibration treatment of 5g, 10g, 15g and 20g and is solidified in a pressure range of 0PMa, the porosity is respectively as follows: 0.67%, 0.48%, 0.85%, 1.51%. After the composite material part subjected to random vibration treatment is cured under the pressure of 0PMa, the internal porosity is close to 1%. When the random vibration acceleration is 10g, compared with a 0MPa part without vibration treatment, the delamination phenomenon in the part is eliminated, and the porosity is reduced from 5.17 percent to 0.48 percent. When the external pressure of the subsequent process reaches 0.1MPa, the porosity is respectively as follows: 0.62%, 0.26%, 0.73%, 0.88%. After vibration treatment and curing in a pressure range of 0.1PMa, the porosity of the interior of the part is less than 1 percent as a whole, wherein the porosity of the interior of the part reaches 0.26 percent at the minimum when the random vibration acceleration is 10g, and the effect of curing and forming the part by an autoclave at 0.6MPa can be achieved. When the external pressure of the subsequent process reaches 0.2MPa, the porosity is respectively as follows: 0.6 percent, 0.28 percent, 0.66 percent and 0.67 percent, and relative to a product with 0.2MPa without vibration treatment, the internal porosity of the product can be reduced from 2.2 percent to 0.25 percent, and the reduction amplitude reaches 87.2 percent. From comparative analysis of interlaminar shear properties, the average interlaminar shear strength of the workpiece subjected to 0.6MPa vibration-free pretreatment is 79.9 MPa. 5g, 10g, 15g and 20g of four parts formed under the vibration acceleration of 0.2MPa, wherein the change trend of the interlaminar shear strength is as follows: 77.1MPa, 81.69MPa, 76.91MPa and 76.7 MPa; the maximum reduction is only 4% relative to 0.6 MPa. The change trend of the interlaminar shear strength of a workpiece which is subjected to four vibration acceleration pretreatments and is formed under 0.1MPa is as follows: the maximum degradation of 78.37MPa, 82.43MPa, 75.71MPa and 71.91MPa relative to 0.6MPa is 8.7%. The change trend of the interlaminar shear strength of a workpiece which is subjected to four vibration acceleration pretreatments and is formed under 0.0MPa is as follows: 71.13MPa, 73.12MPa, 68.57MPa and 60.91MPa, and the average increase of the interlaminar shear performance of the 0MPa workpiece after vibration pretreatment is up to 41.6 percent compared with the interlaminar shear performance of the 0MPa workpiece without vibration pretreatment. The porosity of the composite material part formed in the low-pressure interval after vibration pretreatment is obviously reduced relative to the porosity of the part without vibration pretreatment under low pressure; and the interlaminar shear performance of the product is obviously improved. The invention uses T800/X850 aviation composite material, adopts multidirectional layering based on the principle of standard aviation layering, and obtains a composite material workpiece with porosity lower than 0.3% and interlayer shear strength higher than 80MPa in low-pressure intervals of 0MPa, 0.1MPa and 0.2MPa by utilizing random vibration pretreatment. Compared with the traditional autoclave high-pressure process, the invention provides a novel molding process which utilizes a random vibration pretreatment platform to obtain low-pressure composite material vibration pretreatment and low-pressure curing, can obviously reduce the porosity of a composite material workpiece, improve the performance of the composite material workpiece, and can realize safe, efficient and energy-saving molding and curing of a large composite material workpiece.
Drawings
FIG. 1 is a graph of porosity of a composite article in combination with a low pressure cured article after vibration treatment;
FIG. 2 is a plot of porosity of a composite part cured in an autoclave process;
FIG. 3 is a graph comparing the interlaminar shear strength of composite articles subjected to different vibration treatments at a pressure of 0.2 MPa;
FIG. 4 is a graph comparing the interlaminar shear strength of composite articles subjected to different vibration treatments at a pressure of 0.1 MPa.
Detailed Description
The invention provides a composite material member curing process, which comprises the following steps:
1) heating and insulating the composite material workpiece to be processed in a vibration experiment platform, wherein the heating and insulating treatment is to heat the composite material workpiece to be processed from 30 ℃ to 80 ℃ in the vibration experiment platform at a heating rate of 1.5 ℃/min, and insulating for 30 min; heating and heat preservation are carried out by a nichrome heating wire heater; the vibration frequency interval of the vibration experiment platform is 10HZ-2000 HZ; the temperature range of the vibration experiment platform is-70-200 ℃; the vibration acceleration of the vibration test platform is not more than 50g, and g is 9.8 m/s.
2) In the heating and heat preservation processes, vibration is provided for the composite material workpiece to be processed through a vibration experiment platform; the vibration is 5g-20g, and g is 9.8 m/s;
3) after the vibration is finished, applying low pressure to the composite material workpiece to be processed through a vibration experiment platform, wherein the low pressure is 0-0.2 MPa;
4) in the process of applying low pressure, carrying out secondary heating on the composite material workpiece to be processed, heating the composite material workpiece to be processed from 80 ℃ to 180 ℃ at a heating rate of 1.5 ℃/min, and keeping the temperature for 120 min; the secondary heating adopts a nichrome heating wire heater to heat or preserve heat.
The invention also provides a composite part prepared on the basis of the composite member curing process.
Specifically, the vibration experiment platform adopted by the invention is designed by the university of Chinese defense science and technology, the vibration frequency interval is [10, 2000] HZ, the temperature interval is [ -70 ℃, 200 ℃), and the maximum vibration acceleration is 50 g. The vibration platform utilizes an external air compressor as a power source, continuously utilizes the air hammer to provide a stable vibration source for the mounting platform, and the vibration is transmitted to the composite material part from bottom to top from the mounting platform in the vibration process.
The screenshot process parameters of the composite material member curing process provided by the invention are as follows: in the experiment, the workpiece is heated to 80 ℃ from 30 ℃ in a vibration platform (the temperature rise rate is 1.5 ℃/min, a nichrome heating wire heater is adopted), the temperature is kept for 30min, and the vibration platform provides 5g, 10g, 15g and 20g (g is 9.8m/s) of vibration acceleration in groups in the temperature rise and temperature keeping stages. After the heat preservation is finished (the temperature is not reduced in the process), different groups of vibrating workpieces are heated from 80 ℃ to 180 ℃ for 120min in two vibration-free pressure ranges of 0.1MPa and 0.2MPa (the temperature rise rate is 1.5 ℃/min, and a nichrome heating wire heater is adopted), and the subsequent curing reaction is finished.
Referring to fig. 1 and fig. 2, the composite material part is analyzed by comparing the internal porosity of the autoclave thermocompression cured part in the vibration pretreatment, wherein: after the composite material part is subjected to random vibration treatment of 5g, 10g, 15g and 20g and is solidified in a 0PMa pressure range, the porosity is respectively as follows: 0.67%, 0.48%, 0.85%, 1.51%. After the composite material part subjected to random vibration treatment is cured under the pressure of 0PMa, the internal porosity is close to 1%. When the random vibration acceleration is 10g, compared with a 0MPa part without vibration treatment, the delamination phenomenon in the part is eliminated, and the porosity is reduced from 5.17 percent to 0.48 percent. When the external pressure of the subsequent process reaches 0.1MPa, the porosity is respectively as follows: 0.62%, 0.26%, 0.73%, 0.88%. After vibration treatment and curing in a pressure range of 0.1PMa, the porosity of the interior of the part is less than 1 percent as a whole, wherein the porosity of the interior of the part reaches 0.26 percent at the minimum when the random vibration acceleration is 10g, and the effect of curing and forming the part by an autoclave at 0.6MPa can be achieved. When the external pressure of the subsequent process reaches 0.2MPa, the porosity is respectively as follows: 0.6 percent, 0.28 percent, 0.66 percent and 0.67 percent, and relative to a product with 0.2MPa without vibration treatment, the internal porosity of the product can be reduced from 2.2 percent to 0.25 percent, and the reduction amplitude reaches 87.2 percent.
Referring to FIG. 3 and FIG. 4, from comparative interlaminar shear performance analysis, the average interlaminar shear strength of 0.6MPa workpieces without vibration pretreatment was 79.9 MPa. 5g, 10g, 15g and 20g of four parts formed under the vibration acceleration of 0.2MPa, wherein the change trend of the interlaminar shear strength is as follows: 77.1MPa, 81.69MPa, 76.91MPa and 76.7 MPa; the maximum reduction is only 4% relative to 0.6 MPa. The change trend of the interlaminar shear strength of a workpiece which is subjected to four vibration acceleration pretreatments and is formed under 0.1MPa is as follows: the maximum degradation of 78.37MPa, 82.43MPa, 75.71MPa and 71.91MPa relative to 0.6MPa is 8.7%. The change trend of the interlaminar shear strength of a workpiece which is subjected to four vibration acceleration pretreatments and is formed under 0.0MPa is as follows: 71.13MPa, 73.12MPa, 68.57MPa and 60.91MPa, and the average increase of the interlaminar shear performance of the 0MPa workpiece after vibration pretreatment is up to 41.6 percent compared with the interlaminar shear performance of the 0MPa workpiece without vibration pretreatment. The porosity of the composite material part formed in the low-pressure interval after vibration pretreatment is obviously reduced relative to the porosity of the part without vibration pretreatment under low pressure; and the interlaminar shear performance of the product is obviously improved.
Aiming at the problem of high difficulty in molding and manufacturing caused by high requirements of high-performance large-scale composite parts on curing pressure and uniformity thereof, a novel molding process of 'vibration pretreatment and low-pressure curing' of composite parts is provided. The T800/X850 aviation composite material is used, multidirectional layering is adopted based on the principle of standard aviation layering, and a composite material workpiece with porosity lower than 0.3% and interlayer shear strength higher than 80MPa is obtained in low-pressure intervals of 0MPa, 0.1MPa and 0.2MPa by random vibration pretreatment.
Claims (4)
1. A composite material member curing process is characterized in that: the composite material member curing process comprises the following steps:
1) heating a composite material workpiece to be processed from 30 ℃ to 80 ℃ at a heating rate of 1.5 ℃/min in a vibration experiment platform, and preserving heat for 30 min;
2) in the heating and heat preservation processes, 5g-20g of vibration is provided for a composite material workpiece to be processed through a vibration experiment platform, wherein g is 9.8 m/s;
3) after the vibration is finished, applying low pressure of 0MPa-0.2MPa to the composite material workpiece to be processed through a vibration experiment platform;
4) in the process of applying low pressure, the composite material workpiece to be processed is heated for the second time from 80 ℃ to 180 ℃ at the heating rate of 1.5 ℃/min, and the temperature is preserved for 120min, and the subsequent curing of the composite material workpiece to be processed is completed.
2. The composite material member curing process of claim 1, wherein: and the heating, the heat preservation and the secondary temperature rise are carried out by adopting a nichrome heating wire heater.
3. The composite material member curing process of claim 2, wherein: the vibration frequency range of the vibration experiment platform is 10HZ-2000 HZ; the temperature range of the vibration experiment platform is-70-200 ℃; the vibration acceleration of the vibration test platform is not more than 50g, and g is 9.8 m/s.
4. A composite article prepared based on the composite member curing process of claim 3.
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