CN114179394B - Method for controlling forming of crack stop point of heat insulation layer of end socket of solid rocket engine - Google Patents
Method for controlling forming of crack stop point of heat insulation layer of end socket of solid rocket engine Download PDFInfo
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- CN114179394B CN114179394B CN202111391508.5A CN202111391508A CN114179394B CN 114179394 B CN114179394 B CN 114179394B CN 202111391508 A CN202111391508 A CN 202111391508A CN 114179394 B CN114179394 B CN 114179394B
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- crack stop
- stop point
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- cover layer
- bottom layer
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- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000009413 insulation Methods 0.000 title claims abstract description 21
- 239000007787 solid Substances 0.000 title claims abstract description 14
- 229920001971 elastomer Polymers 0.000 claims abstract description 24
- 239000000463 material Substances 0.000 claims abstract description 19
- 239000004744 fabric Substances 0.000 claims abstract description 7
- 239000003292 glue Substances 0.000 claims abstract description 4
- 238000003892 spreading Methods 0.000 claims abstract description 4
- 230000007480 spreading Effects 0.000 claims abstract description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 12
- 230000003014 reinforcing effect Effects 0.000 claims description 12
- 229920002379 silicone rubber Polymers 0.000 claims description 9
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 7
- LYCAIKOWRPUZTN-UHFFFAOYSA-N Ethylene glycol Chemical compound OCCO LYCAIKOWRPUZTN-UHFFFAOYSA-N 0.000 claims description 6
- 239000006229 carbon black Substances 0.000 claims description 6
- 238000006116 polymerization reaction Methods 0.000 claims description 6
- 229920002545 silicone oil Polymers 0.000 claims description 6
- XOOUIPVCVHRTMJ-UHFFFAOYSA-L zinc stearate Chemical compound [Zn+2].CCCCCCCCCCCCCCCCCC([O-])=O.CCCCCCCCCCCCCCCCCC([O-])=O XOOUIPVCVHRTMJ-UHFFFAOYSA-L 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 238000004073 vulcanization Methods 0.000 claims description 5
- 238000004140 cleaning Methods 0.000 claims description 3
- BPYFPNZHLXDIGA-UHFFFAOYSA-N diphenylsilicon Chemical compound C=1C=CC=CC=1[Si]C1=CC=CC=C1 BPYFPNZHLXDIGA-UHFFFAOYSA-N 0.000 claims description 3
- HIHIPCDUFKZOSL-UHFFFAOYSA-N ethenyl(methyl)silicon Chemical compound C[Si]C=C HIHIPCDUFKZOSL-UHFFFAOYSA-N 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- WGCNASOHLSPBMP-UHFFFAOYSA-N hydroxyacetaldehyde Natural products OCC=O WGCNASOHLSPBMP-UHFFFAOYSA-N 0.000 claims description 3
- UQSXHKLRYXJYBZ-UHFFFAOYSA-N iron oxide Inorganic materials [Fe]=O UQSXHKLRYXJYBZ-UHFFFAOYSA-N 0.000 claims description 3
- NDLPOXTZKUMGOV-UHFFFAOYSA-N oxo(oxoferriooxy)iron hydrate Chemical compound O.O=[Fe]O[Fe]=O NDLPOXTZKUMGOV-UHFFFAOYSA-N 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 239000004945 silicone rubber Substances 0.000 claims description 3
- 239000002994 raw material Substances 0.000 claims description 2
- TXBCBTDQIULDIA-UHFFFAOYSA-N 2-[[3-hydroxy-2,2-bis(hydroxymethyl)propoxy]methyl]-2-(hydroxymethyl)propane-1,3-diol Chemical compound OCC(CO)(CO)COCC(CO)(CO)CO TXBCBTDQIULDIA-UHFFFAOYSA-N 0.000 claims 1
- 230000008602 contraction Effects 0.000 abstract description 4
- 238000007789 sealing Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 8
- 229920002943 EPDM rubber Polymers 0.000 description 7
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 244000043261 Hevea brasiliensis Species 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 229920003052 natural elastomer Polymers 0.000 description 2
- 229920001194 natural rubber Polymers 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 229920006395 saturated elastomer Polymers 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000004898 kneading Methods 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
- 239000004810 polytetrafluoroethylene Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- 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
- B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- 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 discloses a method for controlling the forming of crack stop points of a sealing head heat insulation layer of a solid rocket engine, wherein the sealing head heat insulation layer comprises a cover layer and a bottom layer, a preformed piece is prepared by adopting a rubber material, and the Shore A hardness of the adopted rubber material is 80-90; vulcanizing the preform in a vulcanizing machine to obtain a vulcanized preform; spreading release cloth at the position of the bottom layer debonding, and simultaneously placing the vulcanized preformed piece at the position of a crack stop point to be molded; and (3) adhering and fixing the vulcanized preformed piece with the bottom layer along the opening direction of the cover layer by using glue, and finally integrally vulcanizing and forming. The preformed piece is designed, and an oval structure is formed at the U-shaped crack stop point after forming, so that the stress concentration is eliminated, a certain return stroke is provided for the expansion and contraction of the U-shaped crack stop point, and the integrity of the U-shaped crack stop point structure is effectively ensured.
Description
Technical Field
The invention belongs to the technical field of manufacturing of heat insulation layers of solid rocket engines, and particularly relates to a method for controlling forming of crack stop points of a heat insulation layer of a seal head of a solid rocket engine.
Background
The heat insulating layer of the solid rocket engine is mainly composed of a front end socket heat insulating layer, a rear end socket heat insulating layer and a barrel section heat insulating layer. The heat insulating layers of the front and rear seal heads are important components of the heat insulating structure of the solid rocket engine, and generally comprise various molding process methods such as manual patch, partial mold pressing, integral mold pressing (or autoclave, air bag) molding and the like. The front and rear seal head heat insulating layers generally consist of a cover layer, a bottom layer and a reinforcing layer (a thickened transition area between the cover layer and the bottom layer). Whether the bonding part between the cover layer and the bottom layer is firm or not directly relates to the integrity of the heat insulation structure of the engine after the filling and curing of the engine and in the subsequent storage process, and influences the reliability of the engine in the working process.
The structural form of the crack-stopping point (the root of the artificial debonding layer, i.e. the joint of the cover layer and the bottom layer of the artificial debonding structure) is a key to influence whether the bonding position of the cover layer and the bottom layer is firm or not in the process of filling and storing the engine, and the heat insulation structure keeps integrity. The size of the crack-stop point in the thickness direction of the insulation layer influences the effective thickness of the bottom layer and the cover layer, so that the negative weight of the insulation layer is increased, and the increase of the size along the direction of the bus bar is beneficial to the deformation of the cover layer.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a solid rocket engine head heat insulation layer crack stop point forming control method which can eliminate stress concentration and provide return stroke for expansion and contraction of U-shaped crack stop points.
In order to achieve the purpose, the invention provides a method for controlling the forming of the crack stop point of the seal head heat insulation layer of the solid rocket engine, wherein the seal head heat insulation layer comprises a cover layer and a bottom layer, and the forming control method comprises the following steps:
1) Preparing a preformed piece by adopting a rubber material, wherein the Shore A hardness of the adopted rubber material is 80-90;
2) Vulcanizing the preform in a vulcanizing machine to obtain a vulcanized preform;
3) Spreading release cloth at the position of the bottom layer debonding, and simultaneously placing the vulcanized preformed piece at the position of a crack stop point to be molded; and (3) adhering and fixing the vulcanized preformed piece with the bottom layer along the opening direction of the cover layer by using glue, and finally integrally vulcanizing and forming.
Further, in the step 1), the preformed piece is of a hollow truncated cone structure, and the thickness of the preformed piece is 1-2 mm; the outer diameter of the large end face of the preform is equal to the distance between the break-off start point position of the break-off point and the intersection point position of the cap layer reinforcing region 5, which is equal to the difference of the cap layer reinforcing region length minus the reinforcing region thickness.
Further, in the step 1), the rubber material comprises the following raw materials in parts by weight: 100 parts of methyl vinyl silicone rubber, 0.5-1 part of bis-dipentaerythritol vulcanizing agent, 65-75 parts of gas-phase white carbon black, 6-10 parts of diphenyl silicon glycol control agent, 1-1.7 parts of internal release agent, 0.5-0.8 part of ferric oxide and 0.8 part of glass fiber powder, wherein the internal release agent is compounded by zinc stearate and hydroxyl-terminated silicone oil with low polymerization degree, and the zinc stearate is 0.2-0.5 part and the hydroxyl-terminated silicone oil with low polymerization degree is 0.8-1.2 parts.
Further, in the step 2), the vulcanization temperature is 170 ℃ +/-10 ℃, the vulcanization time is 30-40 minutes, and the pressure is 3-4 Mpa.
Further, in the step 3), a release cloth is laid at a bottom layer position where the preform is placed.
Further, if the cover layer and the bottom layer are the presulfided cover layer and the bottom layer, polishing, cleaning and airing the presulfided cover layer bonding position and the presulfided bottom layer bonding position, placing a piece of raw rubber sheet at the presulfided bottom layer and/or the presulfided cover layer bonding position, and then integrally vulcanizing and forming.
Compared with the prior art, the invention has the following advantages: in the pre-forming process, the pre-forming piece is designed, and an oval structure is formed at the U-shaped crack-stopping point after forming, so that the structure not only eliminates stress concentration, but also provides a certain return stroke for the expansion and contraction of the U-shaped crack-stopping point, and the integrity of the U-shaped crack-stopping point structure is effectively ensured.
Drawings
FIG. 1 is a schematic view of a prior art wedge-shaped crack stop point;
FIG. 2 is a schematic view of a U-shaped crack stopper according to the present invention;
Fig. 3 is an enlarged schematic view of fig. 2 at I.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
The method for controlling the forming of the crack stop point of the sealing head heat insulation layer of the solid rocket engine comprises a cover layer 1 and a bottom layer 2, and the forming control method is as follows:
1) Preparing a preformed piece by adopting a rubber material (polishing, cleaning and airing are needed at the bonding position of the presulfided cover layer and the bonding position of the presulfided bottom layer if the cover layer and the bottom layer are presulfided cover layer and bottom layer);
The preform is of a hollow truncated cone structure, and the thickness of the preform (i.e., the height of the preform) is 1 to 2mm in consideration of the influence on the heat insulating layer and the negative weight of the housing; the outer diameter of the large end surface of the preformed piece is equal to the distance between the detachment starting point position of the fracture stop point and the intersection point position of the cover layer reinforcing region 5, and the intersection point position of the cover layer reinforcing region is equal to the length of the cover layer reinforcing region-the thickness of the reinforcing region;
the Shore A hardness of the rubber material is 80-90;
The preform made of the metal material is stable in size but cannot be stored in the heat insulating layer, and the metal preform needs to be taken out from the crack stopper point after the crack stopper point 3 is formed, so that separate pieces are required to be manufactured as shown in fig. 1 (the forming is also made into a U shape).
The invention adopts rubber material, the preformed piece made of the rubber material does not need to be taken out from the crack stop point, and the last formed crack stop point is U-shaped crack stop point 4, as shown in figures 2 and 3; and because the preformed piece is in a truncated cone structure, the U-shaped fracture-stopping point is in an elliptic structure. Table 1 below gives a comparison of the properties of rubber materials of different shore a hardness formed into U-shaped fracture stops.
Table 1 preformed piece with table of hardness against compression and check point size detection
As can be seen from Table 1, the smaller the dimensional change rate of the U-shaped fracture-stop point, the better the stability as the rubber hardness increases. However, the rubber with a Shore A hardness too high is inferior in plastication and kneading processability, and the Shore A hardness of the rubber material for preparing the preform is 80 to 90 by comprehensively considering the above factors. #
The Shore A hardness of the existing ethylene propylene diene monomer rubber material is generally 72, so that the existing ethylene propylene diene monomer rubber material cannot be used; and the existing ethylene propylene diene monomer heat insulation material is saturated nonpolar rubber.
The ethylene-propylene-diene monomer heat-insulating material is saturated nonpolar rubber, and through experiments, although natural rubber, silicon rubber and ethylene-propylene-diene monomer react to obtain non-adhesive performance, the ethylene-propylene-diene monomer and the ethylene-propylene-diene monomer are easy to adhere, and the silicon rubber has better temperature resistance of the natural rubber, so that the silicon rubber is finally selected as the rubber material of the preformed piece. The invention obtains the high-hardness silicon rubber by improving the silicon rubber, and the formula is as follows:
The weight portion ratio of the components is as follows: 100 parts of methyl vinyl silicone rubber, 0.5-1 part of bis-dipentaerythritol vulcanizing agent, 65-75 parts of gas-phase white carbon black, 6-10 parts of diphenyl silicon glycol control agent, 1-1.7 parts of internal release agent, 0.5-0.8 part of ferric oxide and 0.8 part of glass fiber powder, wherein the internal release agent is compounded by zinc stearate and hydroxyl-terminated silicone oil with low polymerization degree, and the zinc stearate is 0.2-0.5 part and the hydroxyl-terminated silicone oil with low polymerization degree is 0.8-1.2 parts.
Because the gas phase white carbon black has a large influence on the hardness of rubber, referring to Table 2, when the gas phase white carbon black is 65-75 parts, the hardness of the silicon rubber material reaches 80-90 Shore A hardness.
TABLE 2 Effect of white carbon on rubber hardness
| Quantity of white carbon black (parts) | 32 | 47 | 55 | 65 | 70 | 75 |
| Rubber hardness (Shore A) | 35 | 56 | 67 | 80 | 85 | 90 |
2) Vulcanizing the preformed piece in a vulcanizing machine to obtain a vulcanized preformed piece, wherein the vulcanizing temperature is 170+/-10 ℃, the vulcanizing time is 30-40 minutes, and the pressure is 3-4 Mpa; the preform properties after vulcanization were measured as shown in table 3;
TABLE 3 preform Performance test data after curing
| Sequence number | Project | Detection result | Execution standard |
| 1 | Tensile Strength (Mpa) | 4.85 | GB/T528 |
| 2 | Elongation (%) | 79 | GB/T528 |
| 3 | Permanent set (%) | 1.7 | GB/T528 |
| 4 | Shore A hardness | 83 | GB/T531.1 |
| 5 | Density g/cm 3 | 1.469 | GB/T533 |
| 6 | Tear strength KN/m | 5.62 | GB/T529 |
| 7 | Rebound resilience% | 56 | GB/T1681 |
| 8 | Plasticity% | 205 | GB/T12828 |
3) Spreading release cloth at the position of the bottom layer debonding, and simultaneously placing the vulcanized preformed piece at the position of a crack stop point to be molded; in order to firmly fix the vulcanized preformed piece with the bottom layer, the vulcanized preformed piece is adhered and fixed with the bottom layer along the opening direction of the cover layer by using glue, and finally, the preformed piece and the bottom layer are integrally vulcanized and formed;
A release cloth can be independently paved at the bottom layer position of the preform; in the case of a presulfided cover layer and a presulfided base layer, a piece of green sheet is placed in the bonding location of the presulfided base layer and/or presulfided cover layer.
In this example, the adhesive used was a polytetrafluoroethylene glass tape produced by Shanghai Leaching high tech Co., ltd or 730 adhesive produced by Shanghai fine cultural goods Co., ltd with good self-adhesion (the preform was released from the adhesive after curing).
After the U-shaped crack stop point is manufactured through a process test, the effect of the preformed piece on the thicknesses of the cover layer and the bottom layer is the same, namely the thickness of each thinned position of the U-shaped crack stop point of the cover layer and the bottom layer is half of the thickness of the preformed piece.
Compared with a wedge-shaped crack stop point structure, the U-shaped crack stop point structure has the advantages that the preformed piece is designed in the preforming process, an oval structure is formed at the U-shaped crack stop point after forming, stress concentration is eliminated, a certain return stroke amount is provided for the expansion and contraction of the U-shaped crack stop point, and the integrity of the U-shaped crack stop point structure is effectively guaranteed.
When the rubber material with low surface activity is used for the U-shaped crack stop point preformed piece, the invention has the function of debonding, so that debonding treatment can be omitted, and the end socket forming process is simplified. In addition, the nonmetal preformed piece has little influence on the work of the heat insulation layer, and the preformed piece can be taken out without taking out after the U-shaped crack stop point is manufactured. The U-shaped crack stopper is suitable for molding of air bags, autoclave, manual patch seal head heat insulation layers, and molding of integral compression molding seal heads with crack stopper depth less than 1R.
Claims (4)
1. A solid rocket engine seal head heat insulation layer crack arrest point forming control method, the seal head heat insulation layer includes a cover layer and a bottom layer, characterized in that: the molding control method comprises the following steps:
1) Preparing a preformed piece by adopting a rubber material, wherein the Shore A hardness of the adopted rubber material is 80-90; the rubber material comprises the following raw materials in parts by weight: 100 parts of methyl vinyl silicone rubber, 0.5-1 part of bis (dipentaerythritol) vulcanizing agent, 65-75 parts of gas-phase white carbon black, 6-10 parts of diphenyl silicon glycol control agent, 1-1.7 parts of internal release agent, 0.5-0.8 part of ferric oxide and 0.8 part of glass fiber powder, wherein the internal release agent is compounded by zinc stearate and hydroxyl-terminated silicone oil with low polymerization degree, and 0.2-0.5 part of zinc stearate and 0.8-1.2 part of hydroxyl-terminated silicone oil with low polymerization degree are selected;
In the step 1), the preformed piece is of a hollow truncated cone structure, and the thickness of the preformed piece is 1-2 mm; the outer diameter of the large end surface of the preformed piece is equal to the distance between the position of the starting point of the detachment of the U-shaped crack stop point and the intersection point position of the cover layer reinforcing region, and the intersection point position of the cover layer reinforcing region is equal to the difference of the length of the cover layer reinforcing region minus the thickness of the reinforcing region;
2) Vulcanizing the preform in a vulcanizing machine to obtain a vulcanized preform;
3) Spreading release cloth at the bottom layer debonding position, and simultaneously placing the vulcanized preformed piece at the position of a U-shaped crack stop point to be formed; and (3) adhering and fixing the vulcanized preformed piece with the bottom layer along the opening direction of the cover layer by using glue, and finally integrally vulcanizing and forming.
2. The solid rocket engine head heat insulation layer crack stop point forming control method according to claim 1, wherein the method comprises the following steps: in the step 2), the vulcanization temperature is 170+/-10 ℃, the vulcanization time is 30-40 minutes, and the pressure is 3-4 Mpa.
3. The solid rocket engine head heat insulation layer crack stop point forming control method according to claim 1, wherein the method comprises the following steps: in the step 3), a release cloth is laid at the bottom layer position where the preform is placed.
4. The solid rocket engine head heat insulation layer crack stop point forming control method according to claim 1, wherein the method comprises the following steps: if the cover layer and the bottom layer are the presulfided cover layer and the bottom layer, polishing, cleaning and airing the presulfided cover layer bonding position and the presulfided bottom layer bonding position, placing a piece of film stock at the presulfided bottom layer and/or the presulfided cover layer bonding position, and then integrally vulcanizing and forming.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111391508.5A CN114179394B (en) | 2021-11-23 | 2021-11-23 | Method for controlling forming of crack stop point of heat insulation layer of end socket of solid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111391508.5A CN114179394B (en) | 2021-11-23 | 2021-11-23 | Method for controlling forming of crack stop point of heat insulation layer of end socket of solid rocket engine |
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| CN114179394B true CN114179394B (en) | 2024-04-19 |
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| CN114953519B (en) * | 2022-03-27 | 2023-09-15 | 西安航天动力技术研究所 | Single-side crack enhancement simulation piece of artificial debonding structure of solid rocket engine and forming method |
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| CN112497587A (en) * | 2020-10-27 | 2021-03-16 | 湖北三江航天江北机械工程有限公司 | Method for forming heat insulating layer of fiber-wound engine end socket |
| CN113147055A (en) * | 2021-04-28 | 2021-07-23 | 湖北航天技术研究院总体设计所 | Preparation method of composite material shell of solid rocket engine |
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