CN111086128A - Core mold for manufacturing solid rocket engine and forming method thereof - Google Patents
Core mold for manufacturing solid rocket engine and forming method thereof Download PDFInfo
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- CN111086128A CN111086128A CN201911374980.0A CN201911374980A CN111086128A CN 111086128 A CN111086128 A CN 111086128A CN 201911374980 A CN201911374980 A CN 201911374980A CN 111086128 A CN111086128 A CN 111086128A
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- silicone rubber
- silicon rubber
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- solid rocket
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/40—Plastics, e.g. foam or rubber
-
- 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
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
- B29C2033/385—Manufacturing moulds, e.g. shaping the mould surface by machining by laminating a plurality of layers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a core mould for manufacturing a solid rocket engine and a forming method thereof.A core mould main body is assembled by splicing a female mould and a tool, and a reinforcing layer is bonded on the inner surface of the female mould; the reinforced layer is formed by bonding at least one reinforced fabric layer and at least two silicon rubber layers in a staggered manner, wherein the innermost layer and the outermost layer of the reinforced layer are both silicon rubber layers; the reinforcing fabric layer is a two-dimensional or three-dimensional braided fabric for improving the strength of the reinforcing layer; the silicone rubber layer is composed of 70-90% of silicone rubber and 10-30% of silicone rubber reinforcing agent by mass. The invention utilizes the silicon rubber layer to ensure the air tightness of the core mould of the solid rocket engine, adopts the easily deformable reinforced fabric to maintain the size and the external shape of the core mould, and combines the reinforced fabric and the silicon rubber for use, so that the air bag core mould has excellent air tightness and intact external dimension.
Description
Technical Field
The invention belongs to the technical field of solid rocket engine manufacturing, and particularly relates to a core mold for manufacturing a solid rocket engine and a forming method thereof.
Background
The solid rocket engine composite material shell is formed by winding by a wet method, and the winding forming process is to wind continuous carbon fibers soaked in resin glue solution on a core mold under certain tension control according to the modes of longitudinal winding, circumferential winding and the like, and then obtain a solid rocket engine shell finished product through curing and demolding. In the filament winding process, the core mold is the most important supporting structure, and the dimensional accuracy and apparent mass of the shell are related to the core mold. The core mold used for manufacturing the shell of the solid rocket engine at present is a siliceous sand core mold, but the diameter and the loading capacity of the engine are continuously increased along with the continuous improvement of the technical process level of the engine manufacturing, and the appearance of the solid rocket engine with a large diameter and a long structure puts higher requirements on the core mold of the solid rocket engine. The sand core moulds used in the manufacture of the present solid rocket engines still have some disadvantages, such as: the quality is big, the life-span is limited, inconvenient transportation and the inside remaining a large amount of sand grains of casing after the drawing of patterns, the later stage clearance of being not convenient for.
Disclosure of Invention
The invention aims to provide a core mould for manufacturing a solid rocket engine and a forming method thereof, aiming at the problems in the background technology, the core mould is used as a production mould of the solid rocket engine, and can solve the problems of high cost, limited service life and the like of the conventional sand core mould.
The core mould for manufacturing the solid rocket engine comprises a core mould main body and a core mould, wherein the core mould main body is assembled by splicing a female mould and a tool, and a reinforcing layer is bonded on the inner surface of the female mould; the reinforced layer is formed by bonding at least one reinforced fabric layer and at least two silicon rubber layers in a staggered manner, wherein the innermost layer and the outermost layer of the reinforced layer are both silicon rubber layers; the reinforcing fabric layer is a two-dimensional or three-dimensional braided fabric for improving the strength of the reinforcing layer; the silicone rubber layer is composed of 70-90% of silicone rubber and 10-30% of silicone rubber reinforcing agent by mass.
Further, the reinforcing fabric is preferably glass fiber cloth, aramid cloth, carbon fiber cloth, silicone rubber cloth or boron fiber cloth.
Further, the silicone rubber is preferably a room temperature curing condensation type silicone rubber or a room temperature curing addition type silicone rubber. Such as one or more of dimethyl silicone rubber, methyl vinyl phenyl silicone rubber, methyl phenyl silicone rubber, or phenylene silicone rubber.
Further, the silicon rubber reinforcing agent is preferably one or more of fine particle carbon black, white carbon black and silicate.
The forming method of the core mould for manufacturing the solid rocket engine comprises the following steps:
(1) mixing silicon rubber and a silicon rubber reinforcing agent according to a weight ratio, and adding a curing agent;
(2) completely coating the silicon rubber obtained in the step (1) on the inner surface of a female die to form a silicon rubber layer on the inner surface of the female die;
(3) cutting the reinforced fabric layer according to the size of the inner surface of the female die, spraying a surface modifier on the surface of the reinforced fabric layer, and completely attaching one surface of the reinforced fabric layer, which is sprayed with the surface modifier, to the silicone rubber layer;
(4) spraying a surface modifier on the outer surface of the reinforced fabric layer, and coating the silicon rubber obtained in the step (1);
(5) repeating or not repeating the steps (3) to (4) according to actual needs;
(6) and assembling the female die and the tool to obtain the air bag core die.
It should be noted that both the reinforcing fabric layer and the silicone rubber layer should completely cover the inner surface of the female mold.
When the formed core mold is subjected to demolding, firstly, the connecting bolt is removed, and one end of the mold is removed; then removing the connecting nut at the other end of the tool and the die to separate the tool from the die; finally, the core mold is removed from the mold body.
The invention has the following advantages and beneficial effects:
the invention utilizes silicon rubber to ensure the air tightness of the core mould of the solid rocket engine, adopts the easily deformable reinforced fabric to maintain the size and the external shape of the core mould, and combines the reinforced fabric and the silicon rubber for use, so that the air bag core mould has excellent air tightness and intact external dimension.
The invention has the inflatable property on the material, and can fill gas into the air bag core mould when in use; after the core mould is used, the air can be released to recover the core mould of the air bag and be drawn out, so that the core mould can be recycled, and the investment cost of the core mould of the solid rocket engine is reduced.
Compared with a sand core mold, the core mold has the advantages of small mass and convenience in moving and transportation. In the aspect of construction operation, the core mold forming method has the advantages of simple operation and convenient operation.
Detailed Description
The present invention is further illustrated by the following examples, and non-essential modifications and adaptations of the present invention by those skilled in the art in light of the foregoing description are within the scope of the present invention.
Example 1
Cutting the required glass fiber cloth according to the size of the core mold, and spraying silane coupling agent such as KH550, KH560, KH570 and the like on the glass fiber cloth. According to the weight ratio of 10: 1, weighing methyl vinyl silicone rubber and carbon black, stirring uniformly, adding a curing agent such as dicumyl peroxide, uniformly blade-coating the silicon rubber added with the dicumyl peroxide on the inner wall surface of a female die, tightly attaching glass fiber cloth sprayed with a silane coupling agent to the inner surface of the die coated with the silicon rubber to prepare a structure in which one layer of the glass fiber cloth is bonded with one layer of the silicon rubber layer, and then starting the next layer of sizing until a structure in which two layers of the glass fiber cloth and three layers of the silicon rubber layer are bonded in a staggered manner is formed. And finally, splicing and assembling the female die and the tool.
Respectively carry out tensile test to the body of glass fiber cloth to and carry out shear strength test to the shearing sample of two-layer glass fiber cloth and three-layer silicone rubber layer crisscross bonding structure, the experimental data is shown in following table 1~ 2.
TABLE 1 tensile test data for glass fiber cloth body
Table 2 shear strength test data of shear test piece of the staggered bonding structure of this embodiment
In this embodiment, the air tightness data of the airbag core mold having the structure in which two layers of glass fiber cloth and three layers of silicone rubber layers are alternately bonded is shown in table 3.
Table 3 air tightness data of the core mold of this example
| Time (h) | 0 | 2 | 4 | 9 | 15 |
| Air pressure（MPa) | 0.08 | 0.08 | 0.075 | 0.071 | 0.063 |
Example 2
Cutting the needed silicon rubber cloth according to the size of the core mould, and spraying a silane coupling agent on the silicon rubber cloth. According to the weight ratio of 10: 1, weighing methyl vinyl silicone rubber and carbon black, adding diisopropylbenzene hydroperoxide after stirring uniformly, evenly blade-coating the silicone rubber added with the diisopropylbenzene hydroperoxide on the inner wall surface of a female die, closely attaching a silicone rubber cloth sprayed with a silane coupling agent to the inner surface of a die after blade-coating the silicone rubber, preparing a structure in which one layer of the silicone rubber cloth is bonded with one layer of the silicone rubber layer, starting the next layer of sizing until a structure in which two layers of the silicone rubber cloth are bonded with three layers of the silicone rubber layer in a staggered manner is formed, and finally splicing and assembling the die and a tool.
Tensile test is carried out to the body of silicon rubber cloth respectively to and carry out shear strength test to the shearing sample of two-layer silicon rubber cloth and the crisscross bonding structure of three-layer silicon rubber layer, and the experimental data is shown in following table 4~ 5.
Table 4 tensile test data of the silicone rubber cloth body
Table 5 shear strength test data of shear test piece of the staggered bonding structure of this embodiment
The air tightness data of the air bag core mold with the structure of two layers of silicon rubber cloth and three layers of silicon rubber layers which are bonded in a staggered mode in the embodiment are shown in table 6.
Table 6 air tightness data of the core mold of this example
Example 3
Cutting the required aramid fiber cloth according to the size of the core mold, and spraying a silane coupling agent on the aramid fiber cloth. According to the weight ratio of 10: weighing methyl vinyl silicone rubber and carbon black, stirring uniformly, adding hydrogen peroxide diisopropylbenzene, uniformly blade-coating the silicon rubber added with the hydrogen peroxide diisopropylbenzene on the inner wall surface of a female die, closely attaching aramid fiber cloth sprayed with a silane coupling agent to the inner surface of a die after the silicon rubber is blade-coated, preparing a structure in which one layer of aramid fiber cloth is bonded with one layer of silicon rubber layer, starting sizing of the next layer until a structure in which two layers of aramid fiber cloth are bonded with three layers of silicon rubber layers in a staggered manner is formed, and finally splicing and assembling the die and a tool.
Tensile test is carried out on the aramid fabric body, and shear strength test is carried out on shear samples of a structure formed by staggered bonding of two layers of aramid fabric and three layers of silicon rubber layers, and test data are shown in tables 7-8.
Table 7 tensile test data of aramid cloth body
Table 8 shear strength test data of shear test piece of the staggered bonding structure of this embodiment
In this embodiment, the air tightness data of the airbag core mold with the structure of two aramid fabrics and three silicone rubber layers bonded alternately is shown in table 9.
Table 9 air tightness data of the core mold of this example
| Time (h) | 0 | 2 | 4 | 9 | 15 | 17 | 20 |
| Air pressure (MPa) | 0.08 | 0.08 | 0.078 | 0.072 | 0.065 | 0.063 | 0.06 |
Comparative example 1
Cutting the required glass fiber cloth according to the size of the core mold, and spraying a silane coupling agent on the glass fiber cloth. According to the weight ratio of 10: 1, weighing methyl vinyl silicone rubber and carbon black, stirring uniformly, adding hydrogen peroxide diisopropylbenzene, uniformly blade-coating the silicon rubber added with the hydrogen peroxide diisopropylbenzene on the inner wall surface of a female die, tightly attaching glass fiber cloth sprayed with a silane coupling agent to the inner surface of the die coated with the silicon rubber, preparing a structure in which one layer of the glass fiber cloth is bonded with the silicon rubber, then starting the next layer of glue application until a structure in which two layers of the glass fiber cloth and three layers of the silicon rubber are bonded in a staggered manner is formed, finally splicing and assembling the die and a tool, curing, forming and demoulding, and then placing an air bag core die at the temperature of 150 ℃ for treatment for 10 hours. After the high-temperature treatment at 150 ℃ for 10 hours, the tensile test performance of the glass fiber cloth body and the shear strength test of the shear samples of the two layers of glass fiber cloth and the three layers of silicone rubber layers are respectively carried out, and the test data are shown in tables 10-11.
TABLE 10 tensile test data of glass fiber cloth body after high temperature treatment
| Thickness (Single layer cloth) (mm) | Tensile Strength (MPa) | Elongation at Break (%) | |
| 1 | 0.25 | 211.63 | 2.32 |
| 2 | 0.25 | 213.24 | 2.25 |
| 3 | 0.25 | 206.37 | 1.95 |
TABLE 11 shear Strength test data for staggered bond structures after high temperature treatment
The air tightness of the air bag core mold consisting of two layers of glass fiber cloth and three layers of silicon rubber after high-temperature treatment is as shown in the following table.
Table 12 air tightness data of this comparative example mandrel
| Time (h) | 0 | 2 | 4 | 9 | 15 |
| Air pressure (MPa) | 0.08 | 0.078 | 0.074 | 0.07 | 0.064 |
Comparative example 2
Cutting the needed silicon rubber cloth according to the size of the core mould, and spraying a silane coupling agent on the silicon rubber cloth. According to the weight ratio of 10: 1, weighing methyl vinyl silicone rubber and carbon black, adding diisopropylbenzene hydroperoxide after stirring uniformly, evenly scraping the silicone rubber added with the diisopropylbenzene hydroperoxide on the inner wall surface of a female die, closely attaching a silicone rubber cloth sprayed with a silane coupling agent to the inner surface of a die after scraping the silicone rubber, starting the next layer of sizing after preparing a structure that one layer of the silicone rubber cloth is bonded with one layer of the silicone rubber layer until a structure that two layers of the silicone rubber cloth are bonded with three layers of the silicone rubber layer in a staggered manner is formed, finally splicing and assembling the die and a tool, curing, forming and demoulding, and placing an air bag at the temperature of 150 ℃ for processing for 10 hours. After the high-temperature treatment at 150 ℃ for 10 hours, a tensile test is carried out on the silicon rubber cloth body, and a shear strength test is carried out on shear samples of the two layers of silicon rubber cloth and the three layers of silicon rubber layers, wherein the test data are shown in tables 13-14.
TABLE 13 tensile test data of the silicone blanket body after high temperature treatment
TABLE 14 shear Strength test data for staggered bond structures after high temperature treatment
The air tightness of the air bag core mold formed by two layers of silicon rubber cloth and three layers of silicon rubber layers after high-temperature treatment is as shown in the following table.
Table 12 air tightness data of this comparative example mandrel
Comparative examples 1 and 2 are the products of examples 1 and 2, respectively, and the samples and mandrels obtained after high temperature treatment, and comparing the data of examples 1-2 and comparative examples 1-2, it can be seen that the tensile shear properties and the air tightness of the balloon mandrels do not change significantly after the samples and mandrels are subjected to high temperature treatment.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention.
Claims (6)
1. The utility model provides a solid rocket engine makes and uses mandrel, the mandrel main part is assembled by bed die and frock concatenation, characterized by:
the inner surface of the female die is bonded with a reinforcing layer;
the reinforced layer is formed by bonding at least one reinforced fabric layer and at least two silicon rubber layers in a staggered manner, wherein the innermost layer and the outermost layer of the reinforced layer are both silicon rubber layers;
the reinforcing fabric layer is a two-dimensional or three-dimensional braided fabric for improving the strength of the reinforcing layer;
the silicone rubber layer is composed of 70-90% of silicone rubber and 10-30% of silicone rubber reinforcing agent by mass.
2. The core mold for manufacturing a solid rocket engine as recited in claim 1, wherein:
the reinforced fabric is glass fiber cloth, aramid cloth, carbon fiber cloth, silicon rubber cloth or boron fiber cloth.
3. The core mold for manufacturing a solid rocket engine as recited in claim 1, wherein:
the silicone rubber is room temperature curing condensed type silicone rubber or room temperature curing addition type silicone rubber.
4. The core mold for manufacturing a solid rocket engine as recited in claim 1, wherein:
the silicone rubber is one or more of dimethyl silicone rubber, methyl vinyl phenyl silicone rubber, methyl phenyl silicone rubber or phenylene silicone rubber.
5. The core mold for manufacturing a solid rocket engine as recited in claim 1, wherein:
the silicon rubber reinforcing agent is one or more of fine particle carbon black, white carbon black and silicate.
6. The method of forming a core mold for manufacturing a solid rocket engine as recited in claim 1, comprising:
(1) mixing silicon rubber and a silicon rubber reinforcing agent according to a weight ratio, and adding a curing agent;
(2) completely coating the silicon rubber obtained in the step (1) on the inner surface of a female die to form a silicon rubber layer on the inner surface of the female die;
(3) cutting the reinforced fabric layer according to the size of the inner surface of the female die, spraying a surface modifier on the surface of the reinforced fabric layer, and completely attaching one surface of the reinforced fabric layer, which is sprayed with the surface modifier, to the silicone rubber layer;
(4) spraying a surface modifier on the outer surface of the reinforced fabric layer, and coating the silicon rubber obtained in the step (1);
(5) repeating or not repeating the steps (3) to (4) according to actual needs;
(6) and assembling the female die and the tool.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911374980.0A CN111086128A (en) | 2019-12-27 | 2019-12-27 | Core mold for manufacturing solid rocket engine and forming method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911374980.0A CN111086128A (en) | 2019-12-27 | 2019-12-27 | Core mold for manufacturing solid rocket engine and forming method thereof |
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Cited By (3)
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| CN111958887A (en) * | 2020-07-15 | 2020-11-20 | 天津爱思达航天科技有限公司 | High-precision high-yield carbon foam composite material mold and preparation method |
| CN111958886A (en) * | 2020-07-15 | 2020-11-20 | 天津爱思达航天科技有限公司 | Universal carbon foam composite material die with high yield and preparation method thereof |
| CN112008920A (en) * | 2020-07-31 | 2020-12-01 | 湖北三江航天江北机械工程有限公司 | Core mold for producing rocket engine composite material shell and forming method thereof |
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Application publication date: 20200501 |