CN114620999B - Inorganic thermal protection coating repairing material formula for rocket launching pad and application thereof - Google Patents
Inorganic thermal protection coating repairing material formula for rocket launching pad and application thereof Download PDFInfo
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- 239000000463 material Substances 0.000 title claims abstract description 58
- 239000011248 coating agent Substances 0.000 title claims abstract description 33
- 238000000576 coating method Methods 0.000 title claims abstract description 33
- 239000000843 powder Substances 0.000 claims abstract description 42
- 229910052593 corundum Inorganic materials 0.000 claims abstract description 20
- 239000010431 corundum Substances 0.000 claims abstract description 20
- RMAQACBXLXPBSY-UHFFFAOYSA-N silicic acid Chemical compound O[Si](O)(O)O RMAQACBXLXPBSY-UHFFFAOYSA-N 0.000 claims abstract description 14
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000007788 liquid Substances 0.000 claims abstract description 13
- 229910052863 mullite Inorganic materials 0.000 claims abstract description 13
- INJRKJPEYSAMPD-UHFFFAOYSA-N aluminum;silicic acid;hydrate Chemical compound O.[Al].[Al].O[Si](O)(O)O INJRKJPEYSAMPD-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052850 kyanite Inorganic materials 0.000 claims abstract description 11
- 239000010443 kyanite Substances 0.000 claims abstract description 11
- 239000007767 bonding agent Substances 0.000 claims abstract description 8
- 238000002156 mixing Methods 0.000 claims description 12
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 11
- 239000004568 cement Substances 0.000 claims description 11
- 239000002245 particle Substances 0.000 claims description 11
- 239000002994 raw material Substances 0.000 claims description 9
- 238000003756 stirring Methods 0.000 claims description 9
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 8
- 239000011230 binding agent Substances 0.000 claims description 6
- 239000000377 silicon dioxide Substances 0.000 claims description 4
- 238000005303 weighing Methods 0.000 claims description 4
- 229910004298 SiO 2 Inorganic materials 0.000 claims description 3
- 239000000084 colloidal system Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- 239000004482 other powder Substances 0.000 claims description 3
- 229910021487 silica fume Inorganic materials 0.000 claims description 3
- 150000004645 aluminates Chemical group 0.000 claims description 2
- 238000002679 ablation Methods 0.000 abstract description 22
- 238000009413 insulation Methods 0.000 abstract description 8
- 230000007797 corrosion Effects 0.000 abstract description 3
- 238000005260 corrosion Methods 0.000 abstract description 3
- 239000000956 alloy Substances 0.000 abstract description 2
- 229910045601 alloy Inorganic materials 0.000 abstract description 2
- 239000011812 mixed powder Substances 0.000 abstract description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 15
- 230000008439 repair process Effects 0.000 description 11
- 239000007789 gas Substances 0.000 description 5
- 238000002360 preparation method Methods 0.000 description 5
- 230000000052 comparative effect Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 230000032798 delamination Effects 0.000 description 4
- 238000000465 moulding Methods 0.000 description 4
- 229910018072 Al 2 O 3 Inorganic materials 0.000 description 3
- 238000007664 blowing Methods 0.000 description 3
- 239000011247 coating layer Substances 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000011253 protective coating Substances 0.000 description 2
- 239000011819 refractory material Substances 0.000 description 2
- 150000003839 salts Chemical class 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000006703 hydration reaction Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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Abstract
The invention discloses a formula of an inorganic thermal protection coating repairing material for a rocket launching pad and application thereof. The thermal protection coating repairing material consists of powder and liquid bonding agent after grain size grading: the powder adopts three-level granularity matching of corundum fine powder, mullite fine powder and kyanite fine powder, has proper body density, and the maximum granularity of the repairing material is 1mm, and can be used for repairing the area with the reduced thickness of 1-3 mm; the repairing material takes silica sol as a liquid bonding agent, is directly added into the pre-mixed powder, and is smeared for use after being uniformly stirred. The repairing material has the following advantages: 1. the adhesiveness is good: 2. the thermal protection coating repairing material has simple formula and high curing speed. 3. The volume density of the repairing material is low; 4. the repairing material is fast to form; 5. the formed repairing material has certain mechanical strength, certain heat insulation performance and ablation resistance; the molded alloy has excellent corrosion resistance and water resistance, and can be used in the industries of aerospace and the like.
Description
Technical Field
The invention relates to a thermal protection coating repairing material for a rocket launching pad, in particular to an inorganic thermal protection coating surface thinning repairing material for a rocket launching pad, and belongs to the field of high-temperature resistance and thermal insulation protection.
Background
With the development of aerospace industry, in addition to the thermal protection of the aircraft itself, thermal protection measures are added to ground facilities such as rocket launching pads. The domestic rocket launching pad is coated with inorganic refractory materials on the surface of a matrix material to protect the launching pad from thermal ablation and thermal shock of high-temperature gas flow. Because the area of the rocket launching table is larger, partial areas are less influenced by the ablation of the gas flow, and only the thinning of 1-3mm occurs. At present, the treatment mode of the 1-3mm thinning area is that no repair treatment is carried out, and the construction is carried out again after the thickness of the loss reaches more than 6 mm. If the area is not repaired, the ablation resistance of the area is weakened to a certain extent (the ablation resistance and the heat insulation performance may not meet the requirement of protecting the launching pad), and the surface of the area cannot meet the requirement of uniform appearance.
The repairing material is composed of the powder material with the granularity grading and the liquid bonding agent, and can repair the heat protection coating thinned by 1-3mm, ensure the reliability of the ablation resistance of the heat protection coating and ensure the uniformity of the surface appearance of the heat protection coating.
Disclosure of Invention
The invention aims to provide a formula of an inorganic repairing material solidified at normal temperature and application thereof for a rocket launching pad thermal protection coating with a thinning phenomenon. The inorganic heat protection coating repairing material consists of powder material with granularity grading and liquid binding agent.
The invention solves the problems by adopting the following technical scheme:
the graded powder is prepared from the following raw materials in parts by weight, namely 100% in total:
| species of type | Mass ratio |
| Corundum | 52～75％ |
| Mullite | 8～25％ |
| Kyanite | 10～30％ |
| High alumina cement | 3～12％ |
| Alumina micropowder | 1～10％ |
| Silica micropowder | 1～12％ |
The graded powder is preferably prepared from the following components in parts by weight:
the optimal weight ratio of the graded powder is as follows:
| species of type | Mass ratio |
| Corundum | 58～68％ |
| Mullite | 12～20％ |
| Kyanite | 15～25％ |
| High alumina cement | 3～8％ |
| Alumina micropowder | 1～7％ |
| Silica micropowder | 1～8％ |
The corundum is a mixed material obtained by mixing corundum with granularity of 1-0.15mm and corundum with granularity of 100-300 meshes, and the weight ratio of the corundum with granularity of 1-0.15mm to the corundum with granularity of 100-300 meshes in the mixed material is 1: (0.9 to 1.5);
the granularity of the kyanite is 100-300 meshes, preferably 200 meshes;
the granularity of the mullite is 300-400 meshes, preferably 325 meshes;
the high-alumina cement is aluminate cement, preferably Secar71 cement;
the silicon micropowder is silica fume, and the model is 970.
Said Al 2 O 3 The particle size of the fine powder is 400 mesh, preferably the mass content (Al 2 O 3 )≥99.8％。
The liquid binder is silica sol, preferably with a mass content (SiO 2 ) More than or equal to 30 percent, ph is more than or equal to 9, and the average particle size of the colloid particles is equal to or greater than: (8-15 nm).
The weight ratio of the silica sol to the pre-mixed graded powder is 1: (2-8).
The preparation method of the inorganic thermal protection coating repairing material for the rocket launching pad comprises the following steps:
(1) Preparation of graded powder
The grading powder of the rocket launching pad heat protection coating repairing material is characterized in that: the preparation method of the grading powder of the thermal protection coating repairing material comprises the following steps: weighing various raw materials according to the weight ratio, adding 1-0.15mm and 100-300 meshes of corundum powder, 100-300 meshes of kyanite powder and 300-400 meshes of mullite powder, uniformly mixing, stirring in a stirrer for 2-3 minutes, and then adding other powder and stirring for 6-8 minutes so as to ensure uniform mixing of the various raw materials.
(2) Preparation of powder and liquid binder
Silica sol and graded powder are mixed according to the mass ratio of 1: (2-8) stirring for 6-10 min in a stirrer, and then performing construction, coating and repairing.
The invention has the advantages and beneficial effects that:
the invention is prepared by mixing graded powder and silica sol and coating the mixture on a thinned (1-3 mm) thermal protection coating for repairing. The powder adopts 0.15-1 mm corundum with excellent high temperature performance and 100-300 meshes as an aggregate main body, and mullite with excellent 300-400 meshes high temperature performance and good thermal shock resistance is added into the aggregate main body to fill gaps; the addition of the kyanite with 100-300 meshes enhances the volume stability of the repairing material after molding; the alumina micropowder is added, so that the fluidity of the repairing material is increased and the workability is improved due to the filling and dispersion promotion effect of the micropowder. Adding nano silica sol as a binding agent, distributing the silica sol on the surfaces of refractory material particles to form gel around the particles, and combining aggregate and an original thermal protection coating layer together by the gel after molding to form a whole, wherein the gel has stronger bonding performance with the original inorganic thermal protection coating layer; the high alumina cement is added, the hydration reaction of the cement strengthens the strength of the repairing material, and shortens the curing time of the repairing material. The repairing material has certain heat insulation performance and ablation resistance after being molded, and can ensure that the thinned heat protection coating after repairing can still meet the heat protection index of the transmitting table. Is suitable for high humidity, high salt fog and high ultraviolet irradiation environment, and has good corrosion resistance.
Drawings
FIG. 1 back temperature data plot for ablation test;
FIG. 2 is a schematic illustration of repair of the material of the present invention; in the figure: 1 is an inorganic heat protection coating layer, and 2 is a repairing material.
Detailed Description
The invention will be further described with reference to specific examples and accompanying tables, and advantages and features of the invention will become apparent as the description proceeds.
Example 1
1. Preparation of repair material
Weighing 24% of corundum with granularity of 1-0.15mm according to the weight ratio of the powder with granularity grading; 37% corundum with granularity of 100 meshes; 10% of mullite having a particle size of 325 mesh; 19% of kyanite with a particle size of 200 meshes; 6% Secar71 cement; 2% 970% silica fume; 2% of 400 mesh Al 2 O 3 Micro powder;
the mass ratio of the silica sol to the powder with the granularity grading is 1:6. the liquid binder is silica sol, preferably with a mass content (SiO 2 ) More than or equal to 30 percent, ph is more than or equal to 9, and the average particle size of the colloid particles is equal to or greater than: (8-15 nm).
The manufacturing method of the embodiment 1 is as follows: weighing various raw materials according to the weight ratio, adding 1-0.15mm and 100 mesh corundum powder, 200 mesh kyanite powder and 325 mesh mullite powder, uniformly mixing, stirring in a stirrer for 2-3 minutes, and adding other powder, and stirring for 6-8 minutes to ensure uniform mixing of various raw materials.
Silica sol and graded powder are mixed according to the mass ratio of 1: and 6, stirring in a stirrer for 6-10 min, and thus, the construction, coating and repairing can be performed.
2. Application of repair material
(1) Mullite-based thermal protective coating for rocket launching pad was purchased to make 2 blocks of length-width-thickness=190×120×27 mm. (2) Coating the inorganic thermal protection coating repairing material prepared in the step 1 is coated on the 2 blocks of samples with the sizes of 190 multiplied by 120 multiplied by 27mm prepared in the step (1), wherein the coating thickness is 3mm and 1mm respectively.
3. Ablation results
The sample block prepared above was subjected to a test of the back surface temperature of the test piece using a YA6804 type oxygen kerosene engine. Test conditions: engine combustion chamber pressure: pc=1.4±0.05MPa; engine Yu Yang coefficient: α=0.7±0.03; engine nozzle diameter: 65mm; nozzle outlet gas temperature: 2210K; nozzle outlet gas velocity: 2390m/s; combustion chamber temperature: 3470K; ablation test time: 5 s/piece; heat flux density: 17.9Mw/m 2 . The test conditions are that the tail flame blowing condition is simulated when the rocket is launched, and the flame blowing is coated with an inorganic heat protection repair material surface. Testing of uncoated repairTemperature of the material side (back surface temperature). The ablation results are shown in fig. 1: the highest back temperature of 70℃occurs at 223s after ablation of a sample block with a coating thickness of 3mm, and the highest back temperature of 71℃occurs at 232s after ablation of a sample block with a coating thickness of 1mm. The phenomena of delamination and blowing off of the repairing material do not occur in the ablation test process. After the sample block with the coating thickness of 3mm is subjected to an ablation test, the surface of the sample block still has the repair material which is not ablated.
Comparative example 1
1. Mullite-based thermal protective coating for rocket launching pad of the same kind as in example 1 was purchased to prepare a sample block having a size of length-width-thickness=190×120×27 mm.
2. Ablation test for heat insulation of heat insulation adhesive on metal steel plate
The test piece was subjected to the back surface temperature test under the same experimental conditions as in comparative example 1 using the same YA6804 type oxygen kerosene engine as in example 1. The ablation results are shown in fig. 1: the back temperature of the sample block after ablation was at a maximum temperature of 74 ℃ and the time corresponding to the maximum temperature was 193s.
According to the ablation test results of the embodiment 1 and the comparative example 1, we can see that under the same test conditions, the inorganic thermal protection repair material in the patent is respectively coated with 3mm and 1mm in the embodiment 1, and the temperature is reduced by 4 ℃ and 3 ℃ relative to the back temperature of the sample block in the comparative example 1, so that the coating coated with the inorganic repair material has certain ablation resistance and heat insulation performance; in addition, only the ablation phenomenon and no delamination phenomenon of the repair material occur under the action of high-speed gas flow in the test process, which indicates that the bonding force of the repair material and the original coating can meet the requirement.
The granularity of the repairing material is 1mm at most, and the repairing material can be used for repairing the area with the reduced thickness of 1-3 mm; the repairing material takes silica sol as a liquid bonding agent, is directly added into the pre-mixed powder, and is smeared for use after being uniformly stirred. The repairing material has the following advantages: 1. the adhesiveness is good: the repairing material has higher adhesion with the original inorganic thermal protection coating, and has no delamination and delamination phenomenon after repairing. 2. The thermal protection coating repairing material has the advantages of simple formula, easily obtained raw materials, simple production, easy construction, repairability at normal temperature and high curing speed. 3. The repairing material has low volume density, and can not generate excessive residues to cause damage to rocket bodies during rocket launching; 4. the repairing material is quick in molding, and after molding, the repairing material can not generate cracks due to environmental problems (wind, high temperature and insolation), so that the repairing material is suitable for environments with high humidity, high salt mist and high ultraviolet irradiation; 5. the formed repairing material has certain mechanical strength, certain heat insulation performance and ablation resistance; the molded alloy has excellent corrosion resistance and water resistance, and can be used in the industries of aerospace and the like.
Claims (2)
1. An application of a thermal protection coating repairing material for a rocket launching pad is characterized in that: it is composed of powder and liquid binder;
the powder is prepared by mixing the following raw materials in percentage by weight, and the total weight is 100%: 58-68% of corundum, 12-20% of mullite, 19-25% of kyanite, 3-8% of high alumina cement, 1-7% of alumina micro powder and 1-8% of silica micro powder; the granularity of the kyanite is 100-300 meshes;
the liquid bonding agent is silica sol, and the weight ratio of the silica sol to the powder is 1: (2-8);
the repairing material acts on the surface of the rocket launching pad, and the thickness of the inorganic heat protection coating is reduced to be 1-3 mm;
the liquid bonding agent is silica sol, and the mass content of the liquid bonding agent is SiO 2 More than or equal to 30 percent, the pH is more than or equal to 9, and the average particle size of colloid particles is more than or equal to: 8-15 nm;
the powder in the repairing material is prepared from powder with granularity grading, the corundum is a mixed material prepared by mixing corundum with granularity of 1-0.15mm and corundum with granularity of 100-300 meshes, and the weight ratio of the corundum with granularity of 1-0.15mm to the corundum with granularity of 100-300 meshes in the mixed material is 1: (0.9 to 1.5); the granularity of the mullite powder is 300-400 meshes; the high alumina cement is aluminate cement; the silica micropowder is silica fume, and the granularity of the alumina micropowder is 400-450 meshes.
2. The use according to claim 1, characterized in that: the mixing method of the rocket launching pad thermal protection coating repairing material comprises the following steps:
1) Weighing various powder raw materials according to the weight ratio, firstly adding 1-0.15mm and 100-300 meshes of corundum powder, 100-300 meshes of kyanite powder and 300-400 meshes of mullite powder, uniformly mixing, stirring in a stirrer for 2-3 minutes, and then adding other powder and stirring for 6-8 minutes to ensure uniform mixing of various raw materials;
2) The weight ratio of the liquid bonding agent to the premixed powder is 1: (2-8) mixing and stirring for 6-10 min.
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