CN115488019A - Preparation process of solid rocket engine combustion chamber inner wall heat insulation coating - Google Patents
Preparation process of solid rocket engine combustion chamber inner wall heat insulation coating Download PDFInfo
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- CN115488019A CN115488019A CN202211060038.9A CN202211060038A CN115488019A CN 115488019 A CN115488019 A CN 115488019A CN 202211060038 A CN202211060038 A CN 202211060038A CN 115488019 A CN115488019 A CN 115488019A
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- combustion chamber
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- heat
- heat insulation
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 67
- 238000000576 coating method Methods 0.000 title claims abstract description 47
- 239000011248 coating agent Substances 0.000 title claims abstract description 42
- 238000009413 insulation Methods 0.000 title claims abstract description 33
- 239000007787 solid Substances 0.000 title claims abstract description 25
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims abstract description 26
- 238000005488 sandblasting Methods 0.000 claims abstract description 24
- 229910052751 metal Inorganic materials 0.000 claims abstract description 10
- 239000002184 metal Substances 0.000 claims abstract description 10
- 239000003973 paint Substances 0.000 claims abstract description 10
- 238000004381 surface treatment Methods 0.000 claims abstract description 6
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims abstract description 5
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims abstract description 5
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000002679 ablation Methods 0.000 claims abstract description 5
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 5
- 239000011572 manganese Substances 0.000 claims abstract description 5
- 239000002994 raw material Substances 0.000 claims abstract description 5
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 5
- 239000010703 silicon Substances 0.000 claims abstract description 5
- 230000005540 biological transmission Effects 0.000 claims description 4
- 229910052593 corundum Inorganic materials 0.000 claims description 4
- 239000010431 corundum Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 239000003380 propellant Substances 0.000 description 3
- 238000009991 scouring Methods 0.000 description 3
- 238000003763 carbonization Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010923 batch production Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/22—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to internal surfaces, e.g. of tubes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/002—Pretreatement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
- B05D3/0209—Multistage baking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
- B05D3/0254—After-treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/24—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials for applying particular liquids or other fluent materials
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C22/05—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions
- C23C22/06—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH less than 6
- C23C22/07—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH less than 6 containing phosphates
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
- General Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention discloses a preparation process of a solid rocket engine combustion chamber inner wall heat insulation coating, which comprises the following steps: firstly, carrying out sand blasting treatment on the inner wall of the combustion chamber to ensure that the roughness Ra of the inner surface of the combustion chamber after the sand blasting treatment is more than or equal to 8; performing metal surface treatment on the inner wall of the combustion chamber by adopting high-temperature manganese phosphating within 24 hours after the sand blasting treatment on the inner wall of the combustion chamber; then GT-401 organic silicon ablation-resistant paint is used as a coating raw material, and the viscosity of the paint is controlled to be 16 s-24 s by adding alcohol; then, coating the heat-insulating layer on the inner wall of the combustion chamber by adopting a centrifugal roll coating process on the coating prepared in the step 3) within 24 hours after the metal surface treatment of the inner wall of the combustion chamber; and finally, adding the combustion chamber with the inner wall coated with the heat insulation layer in a gradient heating mode to solidify the heat insulation layer on the inner wall of the combustion chamber. The preparation process of the heat insulation coating enables the thickness of the heat insulation layer to reach more than 0.5mm, and improves the thermal protection performance of a combustion chamber.
Description
Technical Field
The invention relates to a preparation process of a solid rocket engine combustion chamber inner wall heat insulation coating, and belongs to the field of solid rocket engines.
Background
In the working process of the solid rocket engine, the temperature of the inner cavity of the combustion chamber can reach 2300-2700 ℃ and is accompanied with high-speed airflow scouring. In order to ensure the normal operation of the solid rocket engine, the heat insulating layer of the combustion chamber needs to be processed or the wall thickness of the combustion chamber needs to be increased. The increase of the wall thickness of the combustion chamber can cause the thrust-weight ratio to be reduced, and the performance of the solid rocket engine is influenced, so that the normal work of the solid rocket engine is ensured by adding the heat insulating layer conventionally. The thermal insulation layer can be generally divided into a lining thermal insulation layer and a coating thermal insulation layer, the lining thermal insulation layer has better high temperature resistance and scouring resistance compared with the coating thermal insulation layer, but the lining structure is generally thicker, so that the filling factor of the solid rocket motor is reduced, the space utilization rate is reduced, and the manufacturing cost is relatively high. The coating type heat insulating layer can be used for processing the heat insulating layer on the inner wall of the special-shaped combustion chamber, the processing technology is simple compared with that of a lining type heat insulating layer, a mold is not needed, the production period is short, but the high temperature resistance and the scouring resistance of the conventional coating type heat insulating layer are low, when the thickness of the heat insulating layer reaches more than 0.5mm, the heat insulating layer is easy to crack and lose effectiveness due to low strength and elongation of the heat insulating layer, so that the heat insulating layer is generally controlled to be less than 0.3mm and is commonly used for the conventional double-base propellant solid rocket engine with the working time not more than 1 s.
Disclosure of Invention
The invention aims to solve the problems that when the thickness of a heat insulation coating on the inner wall of a traditional combustion chamber reaches more than 0.5mm, the heat insulation layer is easy to crack, so that the heat insulation coating fails and the like, and provides a preparation process of the heat insulation coating on the inner wall of the combustion chamber of a solid rocket engine.
The purpose of the invention is realized by the following technical scheme:
the invention discloses a preparation process of a solid rocket engine combustion chamber inner wall heat insulation coating, which comprises the following specific preparation steps:
1) Carrying out sand blasting treatment on the inner wall of the combustion chamber to ensure that the roughness Ra of the inner surface of the combustion chamber after the sand blasting treatment is more than or equal to 8;
2) Performing metal surface treatment on the inner wall of the combustion chamber by adopting high-temperature manganese phosphating within 24 hours after the sand blasting treatment on the inner wall of the combustion chamber;
3) GT-401 organic silicon ablation-resistant paint is used as a coating raw material, and the viscosity of the paint is controlled to be 16 s-24 s by adding alcohol;
4) Coating the heat insulating layer on the inner wall of the combustion chamber by adopting the coating prepared in the step 3) by adopting a centrifugal roll coating process within 24 hours after the metal surface of the inner wall of the combustion chamber is treated;
5) Heating the combustion chamber with the inner wall coated with the heat insulating layer to 80-85 ℃ at the temperature rise rate of 0.6-0.75 ℃/min at room temperature, and preserving the heat for 115-125 min; heating to 100-105 ℃ at the heating rate of 0.8-1.2 ℃/min, and keeping the temperature for 55-65 min; raising the temperature to 115-125 ℃ at a heating rate of 0.8-1.2 ℃/min, preserving the heat for 55-65 min, raising the temperature to 135-145 ℃ at a heating rate of 0.8-1.2 ℃/min, and preserving the heat for 55-65 min; raising the temperature to 155-165 ℃ at the speed of 0.8-1.2 ℃/min, preserving the temperature for 360-600 min, and curing the heat insulating layer on the inner wall of the combustion chamber.
The sand blasting treatment is to select brown corundum with 12-18 meshes as an abrasive and use a press-in sand blasting machine as a power transmission device to perform sand blasting on the inner wall of the combustion chamber.
Advantageous effects
The preparation process of the heat insulation coating realizes the preparation of the heat insulation coating on the inner wall of the combustion chamber of the solid rocket engine working for a long time, ensures that the thickness of the heat insulation layer reaches 0.5-0.8 mm, has no cracking and dropping phenomena, improves the heat protection effect, solves the technical problems of overburning, burnthrough and tearing of the combustion chamber adopting the coating heat insulation layer, and the working time of the solid rocket engine adopting the combustion of the outer side surface of the double base/the outer side surface of the double base as charging is more than or equal to 2s, and improves the heat protection performance of the combustion chamber. The preparation process of the heat insulation coating is simple in processing process, controllable in cost and suitable for batch production.
Detailed Description
The present invention will be further described with reference to the following examples.
Example 1
Carrying out sand blasting treatment on the inner wall of the combustion chamber, selecting 12-mesh brown corundum as an abrasive, and carrying out sand blasting by using a press-in sand blasting machine as a power transmission device, wherein the roughness Ra of the inner surface of the combustion chamber after sand blasting is 9 +/-1; performing metal surface treatment on the combustion chamber by adopting high-temperature manganese phosphating within 24 hours after the sand blasting treatment on the inner wall of the combustion chamber; GT-401 organic silicon ablation-resistant paint is used as a coating raw material, and the viscosity of the paint is controlled within 20s +/-1 s by adding alcohol; coating the heat insulating layer on the inner wall of the combustion chamber by adopting a centrifugal roll coating process on the prepared coating within 24 hours after the metal surface of the inner wall of the combustion chamber is treated; 5) Heating the combustion chamber with the inner wall coated with the heat insulation layer to 80 ℃ at room temperature at the heating rate of 0.6 ℃/min, and preserving the heat for 115min; heating to 100 deg.C at a rate of 0.8 deg.C/min, and maintaining for 55min; heating to 115 ℃ at the heating rate of 0.8 ℃/min, preserving heat for 55min, heating to 135 ℃ at the heating rate of 0.8 ℃/min, and preserving heat for 55min; heating to 155 ℃ at the heating rate of 0.8 ℃/min, preserving the heat for 360min, and curing the heat insulating layer on the inner wall of the combustion chamber; the thickness of the processed heat insulation coating is 0.55mm +/-0.05 mm.
The combustion chamber prepared by the inner wall heat-insulating coating of the example 1 is applied to a solid rocket engine with a certain charge being modified double-base propellant, the diameter of the charge of the engine is 142mm, and the weight of the charge of the engine is 18.5kg; when the solid rocket engine is examined in an inner ballistic test, the working time can reach 2s, the highest temperature outside a combustion chamber is not more than 300 ℃, the phenomena of overburning, burning through and tearing are avoided, the solid rocket engine after working is disassembled, a carbonization layer on the inner wall of the combustion chamber is peeled, and a heat insulation coating is complete and clearly visible, so that the thermal protection performance of the heat insulation coating is stable and reliable.
Example 2
Carrying out sand blasting treatment on the inner wall of the combustion chamber, selecting 12-mesh brown corundum as an abrasive, and carrying out sand blasting by using a press-in sand blasting machine as a power transmission device, wherein the roughness Ra of the inner surface of the combustion chamber after sand blasting is 9 +/-1; performing metal surface treatment on the combustion chamber by adopting high-temperature manganese phosphating within 24 hours after the sand blasting treatment on the inner wall of the combustion chamber; GT-401 organic silicon ablation-resistant paint is used as a coating raw material, and the viscosity of the paint is controlled within 20s +/-1 s by adding alcohol; coating the heat insulating layer on the inner wall of the combustion chamber by adopting a centrifugal roll coating process on the prepared coating within 24 hours after the metal surface of the inner wall of the combustion chamber is treated; heating the combustion chamber with the inner wall coated with the heat insulation layer to 85 ℃ at the room temperature at the heating rate of 0.75 ℃/min, and preserving the heat for 125min; heating to 105 ℃ at the heating rate of 1.2 ℃/min, and keeping the temperature for 65min; heating to 125 deg.C at a rate of 1.2 deg.C/min, maintaining for 65min, heating to 145 deg.C at a rate of 1.2 deg.C/min, and maintaining for 65min; heating to 165 ℃ at the speed of 1.2 ℃/min, preserving heat for 600min, and curing the heat insulating layer on the inner wall of the combustion chamber; the thickness of the processed heat insulation coating is 0.6mm +/-0.05 mm.
The combustion chamber prepared by the inner wall heat-insulating coating in the example 2 is applied to a solid rocket engine with modified double-base propellant as a certain charge, wherein the diameter of the charge of the solid rocket engine is 140mm, and the weight of the charge of the solid rocket engine is 9kg; in the examination of the internal ballistic test of the solid rocket engine, the working time can reach 2s, the highest temperature outside the combustion chamber is not more than 300 ℃, the phenomena of overburning, burning through and tearing do not exist, the solid rocket engine after the work is finished is disassembled, the carbonization layer on the inner wall of the combustion chamber is peeled, the heat insulation coating is complete and clearly visible, and the heat protection performance of the heat insulation coating is stable and reliable.
Claims (2)
1. A preparation process of a solid rocket engine combustion chamber inner wall heat insulation coating is characterized by comprising the following specific preparation steps:
1) Carrying out sand blasting treatment on the inner wall of the combustion chamber to ensure that the roughness Ra of the inner surface of the combustion chamber after the sand blasting treatment is more than or equal to 8;
2) Performing metal surface treatment on the inner wall of the combustion chamber by adopting high-temperature manganese phosphating within 24 hours after the sand blasting treatment on the inner wall of the combustion chamber;
3) GT-401 organic silicon ablation-resistant paint is used as a coating raw material, and the viscosity of the paint is controlled to be 16 s-24 s by adding alcohol;
4) Coating the heat insulating layer on the inner wall of the combustion chamber by adopting the coating prepared in the step 3) by adopting a centrifugal roll coating process within 24 hours after the metal surface of the inner wall of the combustion chamber is treated;
5) Heating the combustion chamber with the inner wall coated with the heat insulating layer to 80-85 ℃ at the temperature rise rate of 0.6-0.75 ℃/min at room temperature, and preserving the heat for 115-125 min; raising the temperature to 100-105 ℃ at a heating rate of 0.8-1.2 ℃/min, and keeping the temperature for 55-65 min; raising the temperature to 115-125 ℃ at a heating rate of 0.8-1.2 ℃/min, preserving the heat for 55-65 min, raising the temperature to 135-145 ℃ at a heating rate of 0.8-1.2 ℃/min, and preserving the heat for 55-65 min; raising the temperature to 155-165 ℃ at the speed of 0.8-1.2 ℃/min, and preserving the heat for 360-600 min to solidify the heat insulating layer on the inner wall of the combustion chamber.
2. The process for preparing the thermal insulation coating on the inner wall of the combustion chamber of the solid rocket engine as claimed in claim 1, wherein the sand blasting treatment is carried out by selecting brown corundum of 12-18 meshes as an abrasive and using a press-in sand blasting machine as a power transmission device to blast the inner wall of the combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211060038.9A CN115488019A (en) | 2022-08-31 | 2022-08-31 | Preparation process of solid rocket engine combustion chamber inner wall heat insulation coating |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211060038.9A CN115488019A (en) | 2022-08-31 | 2022-08-31 | Preparation process of solid rocket engine combustion chamber inner wall heat insulation coating |
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| Publication Number | Publication Date |
|---|---|
| CN115488019A true CN115488019A (en) | 2022-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211060038.9A Pending CN115488019A (en) | 2022-08-31 | 2022-08-31 | Preparation process of solid rocket engine combustion chamber inner wall heat insulation coating |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010150628A (en) * | 2008-12-26 | 2010-07-08 | Toshiba Corp | Heat shielding ceramics coating, and high temperature component-mounted system using the same |
| JP2014092035A (en) * | 2012-10-31 | 2014-05-19 | Mazda Motor Corp | Heat insulation structure of engine combustion chamber member and manufacturing method of the same |
| CN107351414A (en) * | 2016-07-08 | 2017-11-17 | 湖北航天化学技术研究所 | A kind of solid propellant rocket heat insulation layer and its forming method and crowded expanding installation |
| CN107701326A (en) * | 2016-08-08 | 2018-02-16 | 通用汽车环球科技运作有限责任公司 | Explosive motor and the method for coating explosive motor part |
| CN112322040A (en) * | 2020-10-13 | 2021-02-05 | 西安近代化学研究所 | Organic silicon heat insulation layer for engine and preparation method thereof |
| CN114011687A (en) * | 2021-10-08 | 2022-02-08 | 湖北三江航天江河化工科技有限公司 | Method for forming solid rocket engine lining |
-
2022
- 2022-08-31 CN CN202211060038.9A patent/CN115488019A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010150628A (en) * | 2008-12-26 | 2010-07-08 | Toshiba Corp | Heat shielding ceramics coating, and high temperature component-mounted system using the same |
| JP2014092035A (en) * | 2012-10-31 | 2014-05-19 | Mazda Motor Corp | Heat insulation structure of engine combustion chamber member and manufacturing method of the same |
| CN107351414A (en) * | 2016-07-08 | 2017-11-17 | 湖北航天化学技术研究所 | A kind of solid propellant rocket heat insulation layer and its forming method and crowded expanding installation |
| CN107701326A (en) * | 2016-08-08 | 2018-02-16 | 通用汽车环球科技运作有限责任公司 | Explosive motor and the method for coating explosive motor part |
| CN112322040A (en) * | 2020-10-13 | 2021-02-05 | 西安近代化学研究所 | Organic silicon heat insulation layer for engine and preparation method thereof |
| CN114011687A (en) * | 2021-10-08 | 2022-02-08 | 湖北三江航天江河化工科技有限公司 | Method for forming solid rocket engine lining |
Non-Patent Citations (1)
| Title |
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| 陈国光等: "《弹药制造工艺学》", vol. 1, 北京理工大学出版社, pages: 280 - 281 * |
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Application publication date: 20221220 |