CN113997476A - Core mold material for rocket engine grain molding and preparation method thereof - Google Patents
Core mold material for rocket engine grain molding and preparation method thereof Download PDFInfo
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- CN113997476A CN113997476A CN202111209586.9A CN202111209586A CN113997476A CN 113997476 A CN113997476 A CN 113997476A CN 202111209586 A CN202111209586 A CN 202111209586A CN 113997476 A CN113997476 A CN 113997476A
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- 239000000463 material Substances 0.000 title claims abstract description 36
- 238000000465 moulding Methods 0.000 title claims abstract description 25
- 238000002360 preparation method Methods 0.000 title claims abstract description 18
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- 239000004033 plastic Substances 0.000 claims abstract description 29
- 239000000945 filler Substances 0.000 claims abstract description 16
- 239000011159 matrix material Substances 0.000 claims abstract description 13
- 229920000426 Microplastic Polymers 0.000 claims abstract description 12
- 239000000314 lubricant Substances 0.000 claims abstract description 12
- 238000001125 extrusion Methods 0.000 claims abstract description 8
- 238000005469 granulation Methods 0.000 claims abstract description 7
- 230000003179 granulation Effects 0.000 claims abstract description 7
- 239000007787 solid Substances 0.000 claims abstract description 7
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- 239000003963 antioxidant agent Substances 0.000 claims abstract description 5
- 230000003078 antioxidant effect Effects 0.000 claims abstract description 5
- 239000007822 coupling agent Substances 0.000 claims abstract description 5
- 239000002994 raw material Substances 0.000 claims abstract description 3
- 239000012763 reinforcing filler Substances 0.000 claims abstract description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 15
- 238000003801 milling Methods 0.000 claims description 14
- 238000002844 melting Methods 0.000 claims description 12
- 230000008018 melting Effects 0.000 claims description 12
- -1 polypropylene Polymers 0.000 claims description 11
- 239000008187 granular material Substances 0.000 claims description 10
- 238000010438 heat treatment Methods 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 9
- DOIRQSBPFJWKBE-UHFFFAOYSA-N dibutyl phthalate Chemical compound CCCCOC(=O)C1=CC=CC=C1C(=O)OCCCC DOIRQSBPFJWKBE-UHFFFAOYSA-N 0.000 claims description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 7
- 229920002302 Nylon 6,6 Polymers 0.000 claims description 7
- 239000004697 Polyetherimide Substances 0.000 claims description 7
- 239000004917 carbon fiber Substances 0.000 claims description 7
- 239000002041 carbon nanotube Substances 0.000 claims description 7
- 229910021393 carbon nanotube Inorganic materials 0.000 claims description 7
- 238000002156 mixing Methods 0.000 claims description 7
- 229920001601 polyetherimide Polymers 0.000 claims description 7
- 229920006324 polyoxymethylene Polymers 0.000 claims description 7
- 238000007514 turning Methods 0.000 claims description 7
- 229930040373 Paraformaldehyde Natural products 0.000 claims description 6
- 238000003754 machining Methods 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- NLZUEZXRPGMBCV-UHFFFAOYSA-N Butylhydroxytoluene Chemical compound CC1=CC(C(C)(C)C)=C(O)C(C(C)(C)C)=C1 NLZUEZXRPGMBCV-UHFFFAOYSA-N 0.000 claims description 5
- 229920002292 Nylon 6 Polymers 0.000 claims description 5
- 239000004698 Polyethylene Substances 0.000 claims description 5
- 239000004743 Polypropylene Substances 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 5
- 229920003229 poly(methyl methacrylate) Polymers 0.000 claims description 5
- 229920000573 polyethylene Polymers 0.000 claims description 5
- 239000004926 polymethyl methacrylate Substances 0.000 claims description 5
- 229920001155 polypropylene Polymers 0.000 claims description 5
- 239000011231 conductive filler Substances 0.000 claims description 4
- QXYJCZRRLLQGCR-UHFFFAOYSA-N dioxomolybdenum Chemical compound O=[Mo]=O QXYJCZRRLLQGCR-UHFFFAOYSA-N 0.000 claims description 4
- PQXKHYXIUOZZFA-UHFFFAOYSA-M lithium fluoride Chemical compound [Li+].[F-] PQXKHYXIUOZZFA-UHFFFAOYSA-M 0.000 claims description 4
- OPLCSTZDXXUYDU-UHFFFAOYSA-N 2,4-dimethyl-6-tert-butylphenol Chemical compound CC1=CC(C)=C(O)C(C(C)(C)C)=C1 OPLCSTZDXXUYDU-UHFFFAOYSA-N 0.000 claims description 3
- 239000004676 acrylonitrile butadiene styrene Substances 0.000 claims description 3
- 239000002216 antistatic agent Substances 0.000 claims description 3
- ZWYAVGUHWPLBGT-UHFFFAOYSA-N bis(6-methylheptyl) decanedioate Chemical compound CC(C)CCCCCOC(=O)CCCCCCCCC(=O)OCCCCCC(C)C ZWYAVGUHWPLBGT-UHFFFAOYSA-N 0.000 claims description 3
- 235000010354 butylated hydroxytoluene Nutrition 0.000 claims description 3
- 229910021389 graphene Inorganic materials 0.000 claims description 3
- 229910002804 graphite Inorganic materials 0.000 claims description 3
- 239000010439 graphite Substances 0.000 claims description 3
- 239000004417 polycarbonate Substances 0.000 claims description 3
- 229920000515 polycarbonate Polymers 0.000 claims description 3
- 239000004800 polyvinyl chloride Substances 0.000 claims description 3
- 238000009987 spinning Methods 0.000 claims description 3
- ZQZCOBSUOFHDEE-UHFFFAOYSA-N tetrapropyl silicate Chemical compound CCCO[Si](OCCC)(OCCC)OCCC ZQZCOBSUOFHDEE-UHFFFAOYSA-N 0.000 claims description 3
- 238000005303 weighing Methods 0.000 claims description 3
- BOTDANWDWHJENH-UHFFFAOYSA-N Tetraethyl orthosilicate Chemical compound CCO[Si](OCC)(OCC)OCC BOTDANWDWHJENH-UHFFFAOYSA-N 0.000 claims description 2
- 239000006230 acetylene black Substances 0.000 claims description 2
- CJFLBOQMPJCWLR-UHFFFAOYSA-N bis(6-methylheptyl) hexanedioate Chemical compound CC(C)CCCCCOC(=O)CCCCC(=O)OCCCCCC(C)C CJFLBOQMPJCWLR-UHFFFAOYSA-N 0.000 claims description 2
- 239000003365 glass fiber Substances 0.000 claims description 2
- XECAHXYUAAWDEL-UHFFFAOYSA-N acrylonitrile butadiene styrene Chemical compound C=CC=C.C=CC#N.C=CC1=CC=CC=C1 XECAHXYUAAWDEL-UHFFFAOYSA-N 0.000 claims 1
- 229920000122 acrylonitrile butadiene styrene Polymers 0.000 claims 1
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 229920000915 polyvinyl chloride Polymers 0.000 claims 1
- 238000012545 processing Methods 0.000 abstract description 12
- 239000000956 alloy Substances 0.000 abstract description 10
- 229910045601 alloy Inorganic materials 0.000 abstract description 8
- 238000005516 engineering process Methods 0.000 abstract description 5
- 239000000835 fiber Substances 0.000 abstract description 4
- 238000013329 compounding Methods 0.000 abstract description 3
- 238000011068 loading method Methods 0.000 abstract description 2
- 239000003380 propellant Substances 0.000 description 7
- 239000004020 conductor Substances 0.000 description 4
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- 239000011347 resin Substances 0.000 description 4
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- 239000002131 composite material Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
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- 239000004734 Polyphenylene sulfide Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 238000001746 injection moulding Methods 0.000 description 2
- 229920002492 poly(sulfone) Polymers 0.000 description 2
- 229920001707 polybutylene terephthalate Polymers 0.000 description 2
- 229920000139 polyethylene terephthalate Polymers 0.000 description 2
- 239000005020 polyethylene terephthalate Substances 0.000 description 2
- 229920000069 polyphenylene sulfide Polymers 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000002002 slurry Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000006229 carbon black Substances 0.000 description 1
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- 239000002482 conductive additive Substances 0.000 description 1
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- 230000001105 regulatory effect Effects 0.000 description 1
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- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B7/00—Mixing; Kneading
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B9/00—Making granules
- B29B9/02—Making granules by dividing preformed material
- B29B9/06—Making granules by dividing preformed material in the form of filamentary material, e.g. combined with extrusion
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Extrusion Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to the field of conductive plastics, in particular to a core mould material for forming a rocket engine grain and a preparation method thereof, wherein the core mould material comprises the following raw materials in parts by weight: plastic pellets 100; 10-25 parts of high-conductivity filler; 5-15 parts of reinforcing filler; 0.05-0.5 of coupling agent; 0.2-0.8 parts of solid lubricant; 1-5 parts of a plasticizer; 0.2-0.8 percent of antioxidant. By introducing the efficient hyperbranched lubricant containing a large number of end groups and a three-dimensional spherical structure, the filler can be uniformly dispersed only by one-time double-screw granulation. Meanwhile, the surface smoothness of the conductive plastic can be improved, the demolding performance is improved, and the subsequent extrusion molding and processing molding are facilitated. The alloy core mold effectively solves the problems of long processing period, high price, complex processing technology and the like to a certain extent by adopting the technical means of improving the modulus of the matrix by compounding and using good matrix plastic, loading high-conductivity fibers and fillers to enhance the conductivity, adjusting the type and the dosage of the fillers to improve the strength and reduce the linear expansion coefficient.
Description
Technical Field
The invention relates to the field of conductive plastics, in particular to a core mold material for rocket engine grain molding and a preparation method thereof.
Background
The solid rocket engine propellant grain is mainly formed by wall-adhering pouring, wherein a core mold is fixed in an engine, propellant grain slurry is poured on the wall, the propellant grain slurry is subjected to a crosslinking curing reaction at 50-70 ℃, and is demoulded after reaching a certain strength within 3-7 days. The propellant grain is a flammable and explosive hazardous chemical product, static accumulation cannot be generated between the core mould and the propellant grain in the demoulding process, and the range of the resistivity (the surface resistivity is less than or equal to 1.0 multiplied by 107 omega or the bulk resistivity is less than or equal to 1.0 multiplied by 106 omega.m) of the core mould matrix is required to belong to a static conductor.
At present, alloy materials are generally adopted as core mold base materials, in view of the fact that the overall dimension of an engine is larger and larger, the overall shape and the weight of a related core mold component are increased, even if hard aluminum alloy materials with relatively low density are adopted, the weight is larger, the carrying and the assembling are inconvenient, and the danger of falling and smashing personnel or the engine exists. Moreover, the alloy core die has the problems of long processing period, high price, complex processing technology and the like to a certain extent. In order to meet the requirements of mass, low-cost and high-reliability development of future weapon models, development of a novel light high-strength core mold is urgently needed.
The conductive plastic is a conductive composite material formed by using resin as a matrix and conductive filler as filling, and is mainly applied to electronic products, integrated circuit packaging, electromagnetic shielding, conductive/antistatic pipelines, conductive/antistatic plates, conductive films and the like. Compared with metal materials, the conductive material has the advantages of light weight, high forming efficiency, rigidity and toughness, low cost and adjustable resistance value. The conductive additive mainly comprises: carbon fibers, metal powder, stainless steel fibers, carbon nanotubes, graphite, carbon black, graphene, antistatic agents and the like, and the plastic matrix is polypropylene (PP), Polyethylene (PE), polyethylene terephthalate (PET), polyvinyl chloride (PVC), polymethyl methacrylate (PMMA), Polysulfone (PSF), Polyphenylene Sulfide (PPs), Polycarbonate (PC), nylon 6(PA6), nylon 66(PA66), Polyetherimide (PEI), Polyoxymethylene (POM), polybutylene terephthalate (PBT) or acrylonitrile-butadiene-styrene (ABS).
So far, no report on the conductive plastic used for the forming core mould of the propellant grain of the solid rocket engine is found. If conductive plastic is used for the mandrel manufacture, there are a number of problems that need to be solved, such as problem one: the common conductive plastic is usually granulated by adopting a secondary granulation method due to poor mixing degree of the conductive filler and a plastic matrix, the process is complicated, the dispersion uniformity is not good enough, and the conductivity is unsatisfactory, refer to CN101402776B, namely, a conductive plastic and a preparation method, which adopts two plastic matrixes, respectively uses two types of fillers to granulate for two times, then adopts two types of granules to be matched for use according to needs, and carries out secondary granulation by a double screw; and CN107200910A, a high temperature resistant conductive plastic and a preparation method thereof, selects a granular material to add the filler twice, and granulates twice; the second problem is that: the surface smoothness of the common conductive plastic is not enough, the manufactured core die can not meet the requirements of demoulding performance, the manufactured core die is not convenient for subsequent extrusion molding and processing molding, and the surface smoothness is not enough and can not meet the related requirements of friction coefficient; the third problem is that: the composite solid propellant is cured for 3-7 days at 50-70 ℃, and simultaneously contains a certain amount of plasticizer, so that the composite solid propellant has the possibility of penetrating into a plastic core mold, and the core mold is required to have small linear expansion coefficient and strong erosion resistance so as to meet the quality requirement of accurate molding of a grain.
Disclosure of Invention
In order to solve the technical problems, the invention provides a light high-strength core mold material for solid rocket engine grain molding and a preparation method thereof, and the invention adopts the technical means of improving the matrix modulus, loading high-conductivity fibers and fillers to enhance the conductivity, adjusting the types and the dosage of the fillers to improve the strength and reduce the linear expansion coefficient by adopting the good matrix plastic in a compounding way, thereby effectively solving the problems of long processing period, high price, complex processing technology and the like existing in the alloy core mold to a certain extent and meeting the requirements of the mass, low cost and high reliability development of future weapon models.
The technical scheme of the invention is as follows:
a core mold material for rocket engine grain molding is characterized by comprising the following raw materials in parts by weight:
further, the plastic pellet matrix is one of polypropylene (PP), Polyethylene (PE), polyvinyl chloride (PVC), acrylonitrile-butadiene-styrene (ABS), polymethyl methacrylate (PMMA), Polycarbonate (PC), nylon 6(PA6), nylon 66(PA66), Polyetherimide (PEI) and Polyoxymethylene (POM).
Further, the high-conductivity filler is one or more of carbon nanotubes, graphene and an antistatic agent.
Preferably, the high-conductivity filler is carbon nanotubes, and the mesh number is 200-500 meshes, and more preferably 300 meshes.
Further, the reinforcing filler is one or more of carbon fiber, glass fiber and acetylene black, preferably the carbon fiber, and the mesh number is 200-500 meshes, and further preferably 200 meshes.
Further, the coupling agent is one or more of propyl orthosilicate, ethyl orthosilicate, KH-550, KH-560 and KH-570, and the addition amount is preferably 0.3% of the mass of the plastic granules.
Further, the solid lubricant is one or more of graphite, lithium fluoride, molybdenum dioxide and a hyperbranched lubricant, preferably the hyperbranched lubricant, the hyperbranched lubricant product is one or two of HyPer C100, HyPer C181, HyPer C182 and HBP-160 which are produced by Wuhan hyperbranched resin technology Limited company, and preferably one of HyPer C100, HyPer C181 and HyPer C182 is compounded with HBP-160, wherein the compounding ratio is 1: 1; the addition amount is preferably 0.3-0.5% of the mass of the plastic granules.
Further, the plasticizer is one or more of diisooctyl sebacate, dibutyl phthalate and diisooctyl adipate, and the addition amount is preferably 3% of the mass of the plastic granules.
Further, the antioxidant is one or the combination of 2, 4-dimethyl-6-tert-butyl phenol and 2, 6-di-tert-butyl-p-cresol, preferably 2, 6-di-tert-butyl-p-cresol, and the addition amount is preferably 0.6 percent of the mass of the plastic granules.
The invention also provides a preparation method of the core mold material for rocket engine grain molding, which is characterized by comprising the following preparation steps:
plastic granulation: weighing a certain amount of plastic granules, high-conductivity filler, coupling agent, plasticizer and antioxidant according to the weight proportion, premixing, adding into an internal mixer for internal mixing, putting the uniformly internally mixed materials into a double-screw extruder, heating and melting, and then spinning and granulating for later use.
Further, the type of the internal mixer is a plastic pressurized kneader, and the heating and melting temperature is 195-280 ℃;
the invention also provides a preparation method of the core mold for rocket engine grain molding, which is characterized by comprising the following preparation steps:
s1, extrusion forming: heating and melting the prepared core mold material granules by a screw rod and bar extruder, extruding the core mold material granules into a forming mold, and cooling and forming to obtain a core mold column preliminarily;
s2, core die turning and milling: and (4) performing turn-milling modeling on the manufactured column body according to the core mold machining size.
Further, the type of the turn-milling machine tool in the step S2 is a general lathe.
The invention also provides a core mold for rocket engine grain molding, which is characterized by being prepared by the preparation method of the core mold material for rocket engine grain molding.
Compared with the prior art, the invention has the following beneficial effects:
(1) aiming at overcoming the defect of poor mixing degree of the conductive filler and a plastic matrix of the existing conductive plastic by adopting a secondary granulation method, the invention introduces the high-efficiency hyperbranched lubricant containing a large number of end groups and a three-dimensional spherical structure, has strong adsorption capacity on the solid filler, enables the filler to be rapidly dispersed into a high-molecular resin matrix, keeps the dispersion state of powder in the resin matrix, obviously improves the rheological property of the plastic, greatly improves the melt index of the conductive plastic, improves the surface floating fiber, and can uniformly disperse the filler only by once double-screw granulation. Meanwhile, the surface smoothness of the conductive plastic can be improved, the demolding performance is improved, the subsequent extrusion molding and machining molding are facilitated, and the requirements on the surface smoothness and the friction coefficient of the grain core mold can be met.
(2) In the field of propellant charge forming, on the basis of meeting the use requirement, the core mold quality is greatly reduced, and the installation and the use are convenient; the hardness and the conductivity of the plastic can be regulated and controlled by adjusting the filler according to different use requirements; compared with the defect of long processing period of alloy core mold materials, the method can prepare conductive plastic granules for later use, can directly perform hot melting injection molding according to the size requirement of the core mold, and performs turning and milling molding on the molded rods according to the required size, so that the manufacturing cost is 1/4-1/3 of the manufacturing cost of the original metal core mold, and the manufacturing period is shortened by 1/2.
Detailed Description
The present invention will be further described with reference to the following embodiments.
Example 1
A preparation method of a core mold for rocket engine grain forming comprises the following steps:
a. plastic granulation: weighing 10kg of Polyetherimide (PEI) pure material, 1kg of carbon nano tube (300 meshes), 0.5kg of carbon fiber (250 meshes), 0.03kg of propyl orthosilicate, 0.05kg of compounded lubricant HyPer C100 and HBP-160 respectively, 0.3kg of diisooctyl sebacate (industrial grade), 0.02kg of 2, 4-dimethyl-6-tert-butylphenol for premixing, adding the mixture into an internal mixer for internal mixing, putting the uniformly internally mixed material into a double-screw extruder, heating and melting at the screw rotating speed of 167rpm and the temperature of 217 ℃, and then spinning and granulating for later use;
b. extrusion molding: heating the plastic granules prepared in the step a to 195 ℃ by a screw rod extruder, melting, extruding into a forming die, cooling and forming, wherein the size of a formed cylinder is 325 × 125 mm;
c. turning and milling a core die: and (3) performing turn-milling modeling on the manufactured column body according to the core mold machining size, wherein the three-dimensional stroke is an X-coordinate stroke: 400mm, Y coordinate stroke: 150mm, Z coordinate stroke: 150 mm.
The properties of the core mold material for forming the rocket engine grain prepared in this example are shown in table 1:
TABLE 1
Example 2
A preparation method of a core mold for rocket engine grain forming comprises the following steps:
a. plastic granulation: 100kg of Polyformaldehyde (POM) pure material, 18kg of carbon nano tube (400 meshes), 15kg of carbon fiber (300 meshes), 0.5kg of KH-560, 0.8kg of compounded lubricant HyPer C181 and HBP-160 respectively, 5kg of dibutyl phthalate (industrial grade) and 0.5kg of 2, 6-di-tert-butyl paracresol are premixed, added into an internal mixer for internal mixing, the uniformly mixed materials are put into a double-screw extruder, heated and melted at the screw rotating speed of 150rpm and the temperature of 207 ℃ and then are spun and granulated for later use;
b. extrusion molding: heating the granules prepared in the step a to 198 ℃ by a screw rod extruder, melting, extruding into a forming die, and cooling and forming; the molded pillars were 800 × 225 in size;
c. turning and milling a core die: and (3) performing turn-milling modeling on the manufactured column body according to the core mold machining size, wherein the three-dimensional stroke is an X-coordinate stroke: 1000mm, Y-coordinate travel: 250mm, Z coordinate stroke: 250 mm.
The properties of the core mold material for forming the rocket engine grain prepared in this example are shown in table 2:
TABLE 2
Example 3
A preparation method of a core mold for rocket engine grain forming comprises the following steps:
a. plastic granulation: 50kg of nylon 66(PA66) pure material, 12.5kg of carbon nano tube (400 meshes), 2.5kg of carbon fiber (300 meshes), 0.025kg of KH-550, 0.1kg of compounded lubricants HyPer C182 and HBP-160 respectively, 0.5kg of dibutyl phthalate (industrial grade) and 0.4kg of 2, 6-di-tert-butyl paracresol are premixed and added into an internal mixer for internal mixing, the uniformly mixed materials are put into a double-screw extruder, the rotating speed of a screw is 120rpm, the materials are heated and melted at the temperature of 280 ℃ and then are spun and granulated for standby;
b. extrusion molding: heating the granules prepared in the step a to 194 ℃ through a screw rod extruder, melting, extruding into a forming die, and cooling and forming; the molded cylinder size was 325 × 125 mm;
c. turning and milling a core die: and (3) performing turn-milling modeling on the manufactured column body according to the core mold machining size, wherein the three-dimensional stroke is an X-coordinate stroke: 600mm, Y coordinate travel: 150mm, Z coordinate stroke: 150 mm.
The properties of the core mold material for forming the rocket engine grain prepared in this example are shown in table 3:
TABLE 3
The performance test results of the alloy core die prepared by the method of the invention are compared with the performance of the common alloy core die, and the results are shown in table 4:
TABLE 4
As can be seen from Table 4, the resistivity (surface resistivity. ltoreq.1.0X 10) of the core mold prepared by the method of the present invention7Omega or bulk resistivity resistance value less than or equal to 1.0 x 106Ω. m) falls within the range of electrostatic conductors; linear expansion coefficient of core mould is less than or equal to 8 x 10-5The overall performance meets the quality requirement of accurate molding of the grain.
The core mold material can meet the requirement that the density is about half of the density of metal aluminum (1.50 +/-0.1 g/cm3), the resistivity range belongs to an electrostatic conductor, and can be formed by turning and milling, and the size processing precision meets the requirement of GB/T1804-.
The conductive plastic granules are prepared for later use, hot melting injection molding can be carried out according to the size requirement of the core mold, the formed bar is subjected to turn-milling forming according to the required size, the price is 1/4-1/3 of the original alloy core mold cost, the manufacturing period is shortened by 1/2, and the hardness and the conductivity can be customized according to the requirement. The problems of long processing period, high price, complex processing technology and the like of the existing alloy core die are effectively solved, so that the requirements of batch, low-cost and high-reliability development of future weapon models are met.
Claims (10)
1. A core mold material for rocket engine grain molding is characterized by comprising the following raw materials in parts by weight:
2. a mandrel material for rocket motor grain formation as recited in claim 1, wherein said plastic pellet matrix is one of polypropylene, polyethylene, polyvinyl chloride, acrylonitrile butadiene styrene, polymethyl methacrylate, polycarbonate, nylon 6, nylon 66, polyetherimide and polyoxymethylene.
3. The core mold material for rocket motor grain molding according to claim 1, wherein said highly conductive filler is one or more of carbon nanotubes, graphene and antistatic agent.
4. The core mold material for rocket engine grain molding according to claim 1, wherein the reinforcing filler is one or more of carbon fiber, glass fiber and acetylene black.
5. The core mold material for rocket engine grain molding according to claim 1, wherein said solid lubricant is one or more of graphite, lithium fluoride, molybdenum dioxide and "hyperbranched" lubricant.
6. The core mold material for rocket engine grain molding according to claim 1, wherein the coupling agent is one or more of propyl orthosilicate, ethyl orthosilicate, KH-550, KH-560 and KH-570; the plasticizer is one or more of diisooctyl sebacate, dibutyl phthalate and diisooctyl adipate; the antioxidant is one or the combination of 2, 4-dimethyl-6-tert-butylphenol and 2, 6-di-tert-butyl-p-cresol.
7. The method for preparing the core mold material for rocket engine grain molding according to any one of claims 1-7, characterized by comprising the following preparation steps:
plastic granulation: weighing a certain amount of plastic granules, high-conductivity filler, coupling agent, plasticizer and antioxidant according to the weight proportion, premixing, adding into an internal mixer for internal mixing, putting the uniformly internally mixed materials into a double-screw extruder, heating and melting, and then spinning and granulating for later use.
8. The method for preparing a core mold material for rocket engine grain molding as recited in claim 7, wherein the internal mixer is a plastic pressurized kneader, and the melting temperature is 195-280 ℃.
9. A preparation method of a core mold for rocket engine grain molding is characterized by comprising the following preparation steps:
s1, extrusion forming: heating and melting the core mold material granules prepared in any one of claims 7 to 8 by a screw rod extruder, extruding the melted granules into a forming mold, and cooling and forming to obtain a core mold column preliminarily;
s2, core die turning and milling: and (4) performing turn-milling modeling on the manufactured column body according to the core mold machining size.
10. A core mold for rocket engine grain molding, characterized by being produced by the method for producing the core mold material for rocket engine grain molding according to any one of claims 8 to 9.
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