CN109749454B - Preparation method of flexible ablation-resistant composite material of air source micro-foaming carbon layer - Google Patents
Preparation method of flexible ablation-resistant composite material of air source micro-foaming carbon layer Download PDFInfo
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Abstract
The invention provides a preparation method of a flexible ablation-resistant composite material of an air source micro-foaming carbon layer, which is prepared from the following raw materials in parts by weight: 100 parts of silicone rubber, 3-20 parts of fiber, 5-20 parts of white carbon black, 5-80 parts of air source substance, 2-10 parts of curing agent and 0.2-2 parts of catalyst. The flexible ablation-resistant composite material prepared by the invention has excellent heat resistance and ablation resistance and good heat insulation performance, can be used for preparing ablation heat-resistant materials and parts with the requirements on heat resistance and ablation resistance, and is applied to the protection and sealing of structures and parts which need to withstand high-temperature gas, pneumatic heat flow scouring and other severe environments in aerospace aircrafts and related equipment.
Description
Technical Field
The invention relates to the field of composite materials, in particular to a preparation method of a flexible ablation-resistant composite material of a gas source micro-foaming carbon layer.
Background
The ablation-resistant material generates a series of physical and chemical reactions under the condition of gas scouring, such as heat desorption, mass ejection effect of pyrolysis gas, re-radiation of a surface carbon layer and the like, can take away a large amount of heat, reduce the temperature of the protected material and prevent the material from further ablation and damage, and the ablation heat-resistant material has irreplaceable key effects in a space vehicle. With the development of aerospace craft towards faster speed, stronger maneuverability and more complex structure, the traditional rigid heat-proof ablation-resistant material can not completely meet the application requirements, the flexible ablation-resistant material plays an increasingly important role, and plays an increasingly important role in the thermal protection and sealing of some dynamic and complex connecting structures and the matching of large deformation and thermal stress, but the ablation resistance of the conventional flexible material is poor. With the further development of aerospace technology, the development of flexible thermal protection materials with excellent heat resistance, ablation resistance, scouring resistance and other properties has very important significance.
Disclosure of Invention
In order to solve the problems, the invention provides a preparation method of a flexible ablation-resistant composite material of an air source micro-foaming carbon layer, wherein the flexible ablation-resistant composite material is prepared from the following raw materials in parts by weight: 100 parts of silicone rubber, 3-20 parts of fiber, 5-20 parts of white carbon black, 5-80 parts of air source substance, 2-10 parts of curing agent and 0.2-2 parts of catalyst.
Further, the flexible ablation-resistant composite material is prepared from the following raw materials in parts by weight: 100 parts of silicone rubber, 12 parts of fiber, 15 parts of white carbon black, 30-60 parts of air source substance, 3 parts of curing agent and 0.2 part of catalyst.
Further, the flexible ablation-resistant composite material is prepared from the following raw materials in parts by weight: 100 parts of silicon rubber, 12 parts of fiber, 15 parts of white carbon black, 60 parts of gas source substances, 3 parts of curing agent and 0.2 part of catalyst.
Further, the silicon rubber is room temperature vulcanized liquid silicon rubber modified by epoxy resin.
Further, the preparation method of the epoxy resin modified room temperature vulcanized liquid silicone rubber comprises the following steps:
(1) heating epoxy resin and an organic silicon intermediate in an equimolar ratio to 105-155 ℃ under the condition of nitrogen, stirring, dripping 0.1-0.9 wt.% tetraisopropyl titanate after uniformly stirring, and stirring for 5-12 hours to obtain a reaction product;
(2) and adding 10-40 parts of the reaction product into 100 parts of a liquid silicone rubber matrix, uniformly mixing at 100 ℃, and cooling to obtain the silicone rubber.
Further, in the step (1), the epoxy resin is bisphenol A type epoxy resin; the organosilicon intermediate is polymethylphenylsiloxane; and/or in the step (1), the amount of the tetraisopropyl titanate is 0.1-0.9% of the weight of the organosilicon intermediate; and/or in the step (1), the rotating speed of stirring is 400-1000 r/min.
Further, the fiber is aramid fiber, PBO fiber, quartz fiber or carbon fiber; the gas source substance is ammonium borate, dicyandiamide, melamine, ammonium polyphosphate or dicyandiamide-formaldehyde resin; the curing agent is a silane coupling agent; the catalyst is an organic tin compound.
Further, the fibers are quartz fibers; the gas source substance is ammonium borate.
Further, the preparation method comprises the following steps:
(a) weighing the raw materials according to the weight ratio,
(b) gradually adding a small amount of white carbon black into the silicone rubber, and uniformly mixing to obtain a silicone rubber white carbon black mixture; then gradually adding the fiber, the gas source substance and the curing agent into the silicone rubber white carbon black mixture in sequence, and uniformly mixing; finally, adding a catalyst, mixing for 1-5 min, and uniformly mixing to obtain uniformly mixed raw materials;
(c) and putting the uniformly mixed raw materials into a mold, vulcanizing, demolding, sampling, and standing at room temperature for a week to completely cure the raw materials to obtain the product.
Further, in the step (b), the stepwise small-amount addition is a stepwise small-amount addition in a batch; and/or, in the step (b), the step-by-step adding in sequence means that after each same component is added, the other component is added after the same components are uniformly mixed; and/or in the step (c), vulcanizing in a flat vulcanizing machine for 8-36 hours at the vulcanizing temperature of room temperature and under the vulcanizing pressure of 5-15 MPa.
The gas source substance is also called a foaming source and is a nitrogen-containing compound, such as urea, melamine, ammonium polyphosphate and the like, and the gas generated by the gas source substance expands and foams a molten system to form the porous carbon layer.
The flexible ablation-resistant composite material prepared by the invention has excellent heat resistance and ablation resistance and good heat insulation performance, can be used for preparing ablation heat-resistant materials and parts with the requirements on heat resistance and ablation resistance, and is applied to the protection and sealing of structures and parts which need to withstand high-temperature gas, pneumatic heat flow scouring and other severe environments in aerospace aircrafts and related equipment.
It will be apparent that various other modifications, substitutions and alterations can be made in the present invention without departing from the basic technical concept of the invention as described above, according to the common technical knowledge and common practice in the field.
The present invention will be described in further detail with reference to the following examples. This should not be understood as limiting the scope of the above-described subject matter of the present invention to the following examples. All the technologies realized based on the above contents of the present invention belong to the scope of the present invention.
Drawings
FIG. 1 is a thermogravimetric profile (TGA profile) of thermogravimetric analysis of different flexible ablation-resistant composites under nitrogen.
FIG. 2 is a DTG curve of thermogravimetric analysis of different flexible ablation-resistant composites under nitrogen.
Figure 3 is a graph of the line ablation rate and mass ablation rate for different flexible ablation-resistant composites.
Fig. 4 is an SEM image of a cross-section of a carbon layer of different flexible ablation-resistant composites.
Figure 5 is an XRD analysis of the carbon layer after ablation of different flexible ablation-resistant composites.
Fig. 6 is a graph of thermal conductivity results for different flexible ablation-resistant composites.
Fig. 7 is a graph of maximum backplane temperatures for different flexible ablation-resistant composites.
Detailed Description
Examples 1-4 preparation of Flexible ablation-resistant composites of the invention
1. Raw material ratio
TABLE 1 raw material ratios of examples 1 to 4 of the present invention
| Raw materials (parts) | Example 1 | Example 2 | Example 3 | Example 4 |
| |
100 | 100 | 100 | 100 |
| |
12 | 12 | 12 | 12 |
| White carbon black | 15 | 15 | 15 | 15 |
| |
30 | 40 | 50 | 60 |
| Curing agent | 3 | 3 | 3 | 3 |
| Catalyst and process for preparing same | 0.2 | 0.2 | 0.2 | 0.2 |
In table 1, the silicone rubber is an epoxy resin modified room temperature vulcanized liquid silicone rubber, and the preparation method thereof is as follows: adding bisphenol A epoxy resin and an organosilicon intermediate polymethylphenylsiloxane in an equimolar metering ratio into a three-neck flask with a stirrer, introducing nitrogen, starting a stirring device, heating to 105-155 ℃, uniformly mixing the bisphenol A epoxy resin and the organosilicon intermediate polymethylphenylsiloxane, then adding 0.1-0.9 wt.% tetraisopropyl titanate (TPT) dropwise, wherein the dosage of the TPT is 0.1-0.9% of the weight of the organosilicon intermediate, controlling the rotating speed at 400-1000 r/min, stopping stirring after reacting for 5-12 hours, and taking out a reaction Product (PES) for later use. And adding 10-40 parts of PES prepolymer into every 100 parts of liquid silicone rubber matrix, uniformly mixing at 100 ℃, and cooling to obtain the silicone rubber.
In table 1, the curing agent is a silane coupling agent and the catalyst is an organotin compound.
2. Preparation method
Weighing the raw materials according to the weight ratio, gradually adding a small amount of white carbon black (gradually adding a small amount of white carbon black in batches) into the silicon rubber, and mechanically stirring until the mixture is substantially uniform; then, mixing for a certain time by using a three-roller grinding machine to uniformly disperse the white carbon black in the silicon rubber; sequentially and gradually adding quartz fiber, ammonium borate and a curing agent in corresponding proportion (adding another component after adding the same component and uniformly mixing) into the silicon rubber and white carbon black mixture, uniformly mixing the mixture by using a laboratory miniature kneader for a certain time, finally adding a catalyst with corresponding content, mixing the mixture for 1-5 minutes, putting the mixture into a mold, vulcanizing the mixture in a flat vulcanizing machine for 8-36 hours (room temperature, 5-15 MPa), demolding and sampling, and standing the mixture at room temperature for one week to completely cure the mixture to obtain the silicon rubber and white carbon black composite material.
3. Examples 1-4 preparation of Flexible ablation-resistant composites
The flexible ablation-resistant composite materials of examples 1-4 were prepared according to the raw material ratios shown in table 1 and by the preparation method described in example "2", and were respectively named as S30, S40, S50, and S60 according to the content of ammonium borate.
Comparative example 1 preparation of composite Material
1. Raw material ratio
100 parts of silicon rubber, 12 parts of quartz fiber, 15 parts of white carbon black, 3 parts of curing agent and 0.2 part of catalyst. The types of silicone rubber, quartz fiber, white carbon black, curing agent and catalyst are the same as in the examples.
2. Preparation method
The preparation method is the same as that of the embodiment: weighing the raw materials according to the proportion, gradually adding a small amount of white carbon black (gradually adding a small amount of white carbon black in batches) into the silicon rubber, and mechanically stirring until the mixture is substantially uniform; then, mixing for a certain time by using a three-roller grinding machine to uniformly disperse the white carbon black in the silicone rubber; sequentially and gradually adding quartz fiber and a curing agent in corresponding proportion (adding another component after adding the same component to be uniformly mixed) into the silicon rubber and white carbon black mixture, uniformly mixing the mixture by using a laboratory miniature kneader for a certain time, finally adding a catalyst with corresponding content to be mixed for 1-5 minutes, putting the mixture into a mold, vulcanizing the mixture in a flat vulcanizing machine for 8-36 hours (room temperature, 5-15 MPa), demolding and sampling, and standing the mixture at room temperature for a week to completely cure the mixture to obtain the silicon rubber and white carbon black composite material. The resulting flexible ablation-resistant composite was designated S0.
Comparative example 2 preparation of composite Material
1. Raw material ratio
100 parts of silicon rubber, 6 parts of curing agent and 0.8 part of catalyst. The types of silicone rubber, curing agent and catalyst were the same as in the examples.
2. Preparation method
The preparation method is the same as that of the embodiment: weighing the raw materials according to the proportion as required, adding a curing agent into the silicon rubber, uniformly stirring, adding a catalyst with corresponding content, mixing for 1-5 minutes, placing the mixture in a vacuum oven for vacuumizing to remove bubbles, placing the mixture in a mold, vulcanizing in a flat vulcanizing machine for 8-36 hours (the vulcanization temperature is room temperature, and the pressure is 5-15 MPa), demolding, sampling, and placing at room temperature for one week to completely cure the mixture. The composite material obtained by preparation is named Pure.
The advantageous effects of the present invention are described below by way of test examples.
Test example 1 thermogravimetric analysis of a flexible ablation-resistant composite material according to the invention
1. Test method
Thermogravimetric analysis was performed on the flexible ablation-resistant composite materials prepared in examples 1 to 4 and comparative examples 1 to 2 under a nitrogen atmosphere. The temperature range tested was: room temperature to 800 ℃; the heating rate is as follows: 10 ℃/min; the atmosphere is: under the condition of nitrogen; the instrument comprises the following steps: TG209F1, NETZSCH, usa.
2. Test results
The thermogravimetric analysis results of each group of flexible ablation-resistant composite materials are shown in table 2 and fig. 1-2.
TABLE 2 residual weight of each group of flexible ablation-resistant composite materials at 800 ℃ for thermal degradation
| Test specimen | Pure | S0 | S30 | S40 | S50 | S60 |
| R800(％) | 11.58 | 14.97 | 17.69 | 27.49 | 36.17 | 38.89 |
As can be seen from fig. 1, fig. 2 and table 2, the addition of ammonium borate significantly changes the thermal degradation process of the composite material, significantly inhibits the mass loss of the silicone rubber at a higher temperature, and increases the residual weight of the composite material at 800 ℃, that is, the addition of ammonium borate significantly improves the heat resistance of the composite material. Under the severe environment of ablation, the high heat resistance of the composite material is beneficial to carbon formation to form a more stable carbon layer or ceramic layer to resist the erosion of high-temperature and high-pressure heat flow, and the invasion of external heat and oxygen to the internal material is slowed down or isolated, so that the ablation resistance of the composite material is improved.
Test example 2 research on ablation resistance of Flexible ablation-resistant composite Material of the present invention
1. Test method
The flexible ablation-resistant composite materials prepared in examples 1-4 and comparative examples 1-2 were used to test the ablation resistance. The ablation resistance is tested by adopting an oxyacetylene ablation testing device, the surface of the sample is vertically blasted by adopting oxyacetylene flame, the ablation time is 30s, the ablation temperature is more than 2700 ℃, the sample is naturally cooled to the normal temperature after ablation is finished, and a surface carbon layer is stripped. And measuring the thickness and mass changes of the sample before and after the experiment, and calculating the linear ablation rate and the mass ablation rate of the sample. The calculation formula is as follows:
LAR＝△d/t＝(d1-d2)/t MAR＝△m/t＝(m1-m2)/t
LAR-ablation rate of sample wire, mm/s;
MAR-sample mass ablation rate, g/s;
d 1-original thickness of specimen, mm;
d 2-thickness of sample after ablation, mm;
m 1-original mass of specimen, g;
m 2-mass after sample ablation, g;
t-ablation time, s.
The carbon layer cross-sections of the flexible ablation-resistant composites of examples 1-4 and the composite of comparative example 1 after ablation were observed using a Scanning Electron Microscope (SEM).
The carbon layers peeled off after ablation of the flexible ablation-resistant composites of examples 1 to 4 and the composite of comparative example 1 were ground into powder in a mortar, and subjected to X-ray diffraction (XRD) (DY1291, philips, netherlands) analysis, with a 2 θ range of 5 to 85 °.
2. Test results
The ablation resistance of each set of flexible ablation-resistant composites is shown in figure 3 and in table 3.
TABLE 3 line ablation Rate results for each set of Flexible ablation resistant composites
As can be seen from fig. 3 and table 3, the flexible ablation-resistant composite material prepared according to the present invention has a low ablation rate, and the ablation rate of the flexible ablation-resistant composite material prepared according to the present invention is significantly reduced compared to comparative examples 1 and 2. As shown by the dashed lines in fig. 3, for the optimal combination S60 (line ablation rate minimum), the line ablation rate was reduced by 78.98% and 34.11% compared to Pure and S0, respectively. The smaller the line ablation rate means the better the ablation performance, and for the ablation material, after the high-temperature resistant fiber is added, the further obvious reduction of the line ablation rate is difficult, so the obvious reduction shows that the ablation resistance of the composite material is obviously improved in the optimal combination. The test result shows that the flexible ablation-resistant composite material prepared by the invention has good ablation resistance, and compared with the composite material prepared by the comparative example, the ablation resistance is obviously improved.
Fig. 4 is a cross-sectional view of the carbon layer after ablation of each group of flexible ablation-resistant composite materials, and as can be seen from the SEM image in fig. 4, the carbon layer has a microporous structure, and the microporous structure is favorable for reducing the thermal conductivity of the carbon layer, so that the linear ablation rate of the composite material is reduced, that is, the ablation resistance of the composite material is improved.
As can be seen from fig. 5, after the flexible ablation-resistant composite material prepared by the present invention is ablated, the carbon layer is mainly composed of SiC ceramic material and graphite. With the increase of the addition amount of the ammonium borate, the content of the SiC in the ceramic component is gradually reduced, which shows that the ammonium borate is beneficial to the carbonization of the ablation layer material. Under the ablation environment, the ablation layer is quickly carbonized to form a stable carbon layer with certain strength, so that the erosion damage of high-temperature gas and pneumatic heat flow can be resisted, and the ablation resistance of the composite material is improved.
Test example 3 study on thermal conductivity of flexible ablation-resistant composite material of the invention
1. Test method
The thermal conductivity and the maximum backboard temperature of the flexible ablation-resistant composite materials prepared in the examples 1-4 and the comparative examples 1-2 were measured. The thermal conductivity of the composite material is measured by adopting a heat conduction tester (Hot Disk TPS 2500, Sweden), and a thermocouple probe is simultaneously used as a heat source and a temperature sensor; and (3) adhering the K-type thermocouple to the back of the sample by using a high-temperature adhesive tape, recording the temperature change of the back of the sample in the ablation process by using a temperature tester, and taking the maximum value of the measured temperature as the temperature of the back plate of the sample.
2. Test results
The heat conduction performance results of different flexible ablation-resistant composite materials are shown in fig. 6-7 and table 4.
TABLE 4 Heat transfer Performance results for Flexible ablation-resistant composites
The result of the heat conductivity of the flexible ablation-resistant composite material of the invention shows that: the composite material system has lower heat conductivity and backboard temperature, the low heat conductivity can effectively delay or inhibit the invasion of external heat, can play a good role in protecting internal materials, reduces the linear ablation rate of the composite material, and improves the ablation resistance of the composite material; the lower back plate temperature avoids thermal damage to the target shield material. Therefore, the flexible ablation-resistant composite material has good ablation resistance.
In conclusion, the flexible ablation-resistant composite material prepared by the invention has excellent heat resistance and ablation resistance and good heat insulation performance, can be used for preparing ablation heat-resistant materials and parts with the requirements on heat resistance and ablation resistance, and is applied to the protection and sealing of structures and parts which need to withstand high-temperature gas, pneumatic heat flow scouring and other severe environments in aerospace aircrafts and related equipment.
Claims (6)
1. A preparation method of a flexible ablation-resistant composite material of an air source micro-foaming carbon layer is characterized by comprising the following steps: the flexible ablation-resistant composite material is prepared from the following raw materials in parts by weight: 100 parts of silicone rubber, 12 parts of fiber, 15 parts of white carbon black, 30-60 parts of air source substance, 3 parts of curing agent and 0.2 part of catalyst;
the fiber is quartz fiber; the gas source substance is ammonium borate; the curing agent is a silane coupling agent; the catalyst is an organic tin compound;
the silicon rubber is room temperature vulcanized liquid silicon rubber modified by epoxy resin.
2. The production method according to claim 1, characterized in that: the flexible ablation-resistant composite material is prepared from the following raw materials in parts by weight: 100 parts of silicon rubber, 12 parts of fiber, 15 parts of white carbon black, 60 parts of gas source substances, 3 parts of curing agent and 0.2 part of catalyst.
3. The production method according to claim 1 or 2, characterized in that: the preparation method of the epoxy resin modified room temperature vulcanized liquid silicone rubber comprises the following steps:
(1) heating bisphenol A type epoxy resin and polymethylphenylsiloxane in an equimolar ratio to 105-155 ℃ under the condition of nitrogen, stirring, dripping 0.1-0.9 wt.% of tetraisopropyl titanate after uniformly stirring, and stirring for 5-12 hours to obtain a reaction product;
(2) and adding 10-40 parts of the reaction product into 100 parts of a liquid silicone rubber matrix, uniformly mixing at 100 ℃, and cooling to obtain the silicone rubber.
4. The production method according to claim 3, characterized in that: in the step (1), the amount of the tetraisopropyl titanate is 0.1-0.9% of the weight of the polymethylphenylsiloxane; and/or in the step (1), the rotating speed of stirring is 400-1000 r/min.
5. The production method according to claim 1 or 2, characterized in that: the preparation method comprises the following steps:
(a) weighing the raw materials according to the weight ratio of claim 1 or 2,
(b) gradually adding a small amount of white carbon black into the silicone rubber, and uniformly mixing to obtain a silicone rubber white carbon black mixture; then sequentially and gradually adding the fiber, the gas source substance and the curing agent into the silicon rubber and white carbon black mixture, and uniformly mixing; finally, adding a catalyst, mixing for 1-5 min, and uniformly mixing to obtain uniformly mixed raw materials;
(c) and putting the uniformly mixed raw materials into a mold, vulcanizing, demolding, sampling, and standing at room temperature for a week to completely cure the raw materials to obtain the product.
6. The method of claim 5, wherein: in the step (b), the stepwise small-amount addition is a stepwise small-amount addition in small portions; and/or, in the step (b), the step-by-step adding in sequence means that after each same component is added, the other component is added after the same components are uniformly mixed; and/or in the step (c), vulcanizing in a vulcanizing press for 8-36 hours at room temperature and under the vulcanizing pressure of 5-15 MPa.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1031413A2 (en) * | 1999-02-26 | 2000-08-30 | Agfa-Gevaert AG | Radiation-sensitive recording material for the production of waterless offset printing plates |
| CN103087531A (en) * | 2013-01-22 | 2013-05-08 | 辽宁科瑞德电缆有限公司 | Fire retardant foaming material for halogen-free flame retardant cable and preparation method of fire retardant foaming material |
| CN105754352A (en) * | 2016-05-12 | 2016-07-13 | 王维娜 | Flame-retardant fire-resistant power cable material and preparation method thereof |
| CN106046386A (en) * | 2016-08-08 | 2016-10-26 | 四川大学 | Epoxy resin-organosilicon polymer and preparation method and application thereof |
| CN107686559A (en) * | 2017-09-29 | 2018-02-13 | 西安近代化学研究所 | A kind of engine composite adiabatic layer |
-
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1031413A2 (en) * | 1999-02-26 | 2000-08-30 | Agfa-Gevaert AG | Radiation-sensitive recording material for the production of waterless offset printing plates |
| CN103087531A (en) * | 2013-01-22 | 2013-05-08 | 辽宁科瑞德电缆有限公司 | Fire retardant foaming material for halogen-free flame retardant cable and preparation method of fire retardant foaming material |
| CN105754352A (en) * | 2016-05-12 | 2016-07-13 | 王维娜 | Flame-retardant fire-resistant power cable material and preparation method thereof |
| CN106046386A (en) * | 2016-08-08 | 2016-10-26 | 四川大学 | Epoxy resin-organosilicon polymer and preparation method and application thereof |
| CN107686559A (en) * | 2017-09-29 | 2018-02-13 | 西安近代化学研究所 | A kind of engine composite adiabatic layer |
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