CN110566366B - Combined core mold structure for rocket engine grain molding and use method thereof - Google Patents
Combined core mold structure for rocket engine grain molding and use method thereof Download PDFInfo
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- CN110566366B CN110566366B CN201910825359.5A CN201910825359A CN110566366B CN 110566366 B CN110566366 B CN 110566366B CN 201910825359 A CN201910825359 A CN 201910825359A CN 110566366 B CN110566366 B CN 110566366B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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Abstract
The invention discloses a combined core mold structure for rocket engine grain forming and a use method thereof, wherein a plurality of special-shaped gaps are arranged on the side surface of a grain, the structure comprises a plurality of groups of special-shaped assemblies, the groups of special-shaped assemblies and the grain special-shaped gaps are matched to form a cylinder, each group of special-shaped block assemblies are circumferentially provided with a first special-shaped block and a second special-shaped block, and the first special-shaped block is in contact with the grain to be formed and is a metal piece; the second special-shaped block is positioned on one side of the first special-shaped block, which is far away from the grain, and is made of silicon rubber, and the size of the thickest part of the first special-shaped block is smaller than the minimum size of a demoulding opening in rocket engine grain forming; the structure further comprises a molded rubber sleeve and a positioning transition ring, wherein the end face of the molded rubber sleeve clamps the end face of the second special-shaped block, and the end face of the positioning transition ring clamps the end face of the first special-shaped block and the molded rubber sleeve. By adopting the structure and the method, the propellant charging of the small inner bore explosive type engine can be well adapted, the assembly efficiency is high, the quality is stable, and the reliability is good.
Description
Technical Field
The invention belongs to the technical field of rocket engine charging, and particularly relates to a combined core mold structure for rocket engine grain forming and a using method thereof.
Background
In order to enable a solid rocket engine to have good internal ballistic performance, a special-shaped explosive type combining a conical groove type and a wing column type appears in the explosive type design of a certain small engine, the explosive type of the engine generally adopts a metal combined core mould to form the explosive type surface, the existing metal combined core mould comprises wings, connecting pieces, a fixed cylinder, a cover piece, a positioning ring and a transition ring, and all the parts are spliced to form a complete core mould structure; the metal core moulds are reasonably combined and connected into a whole in the engine combustion chamber before charging, and are taken out in a blocking and splitting manner during demoulding to form a complete medicine type structure. For the special explosive type with the tail special-shaped structure, the operation requirements of assembly, demolding and disassembly cannot be met due to the structural size of the shell, and the special explosive type with the tail special-shaped structure is suitable for charging of a smaller inner hole explosive type engine. Because of the demand of slurry pouring, can not directly shaping the medicine profile, need the shaping of ground paste solidification back to ensure the grain structure, the shaping process brings very high safe risk again, also has the difficulty to the uniformity of assurance quality.
Solid engines generally use a core mold to form the molded surface, and for a complicated inner molded surface, a combined core mold is used. In order to meet the operation requirements of assembly and demolding disassembly, a certain operation space must be provided for the combined core mold fastener.
In order to meet the requirements of thrust ratio and mass ratio, a rocket engine propellant special-shaped explosive type is developed, the three-dimensional structure of the rocket engine propellant special-shaped explosive type is shown in figure 1, a plurality of special-shaped notches are arranged on the side surface of an explosive column, and the requirement for disassembly cannot be met due to the fact that the maximum width size of a special-shaped block is larger than the maximum demolding space, so that the assembly and subsequent demolding of a mold are difficult.
Disclosure of Invention
The invention provides a special-shaped silicon rubber combined core mold structure and a using method thereof, which can be well suitable for propellant charging of a small inner-hole explosive type engine, and have the advantages of high assembly efficiency, stable quality and good reliability.
The invention adopts the technical scheme that a combined core mold structure for rocket engine grain forming is provided with a plurality of special-shaped gaps on the side surface of a grain, the structure comprises a plurality of groups of special-shaped assemblies, the groups of special-shaped assemblies and the grain special-shaped gaps are matched to form a cylinder, each group of special-shaped block assemblies are provided with a first special-shaped block and a second special-shaped block along the circumferential direction, and the first special-shaped block is in contact with the grain to be formed and is a metal piece; the second special-shaped block is positioned on one side of the first special-shaped block, which is far away from the grain, and is made of silicon rubber, and the size of the thickest part of the first special-shaped block is smaller than the minimum size of a demoulding opening in rocket engine grain forming; the structure further comprises a molded rubber sleeve and a positioning transition ring, wherein the end face of the molded rubber sleeve clamps the end face of the second special-shaped block, and the end face of the positioning transition ring clamps the end face of the first special-shaped block and the molded rubber sleeve.
Furthermore, a positioning step is arranged on the side, close to the second special-shaped block, of the first special-shaped block, a positioning groove is arranged on the side, close to the first special-shaped block, of the second special-shaped block, and the positioning step is connected with the positioning groove in a matched mode.
Furthermore, a double-sided adhesive layer is arranged on the contact surface of the first special-shaped block and the second special-shaped block.
Furthermore, the end face, close to the positioning transition ring, of the first special-shaped block is provided with a positioning pin and a threaded hole, and the end face, close to the first special-shaped block, of the positioning transition ring is provided with a positioning hole corresponding to the positioning pin and a bolt matched with the threaded hole.
Furthermore, the end of the positioning transition ring close to the first profile block is of an inclined surface structure, and the thickness of the end part gradually increases from the center of the positioning transition ring to the outer side.
Further, the second profile block is close to one end of the formed rubber sleeve to one end far away from the formed rubber sleeve, and the thickness size is gradually reduced. The maximum difference in thickness is less than 0.2 mm.
Furthermore, the molded rubber sleeve is of an annular structure, and the width of one end face of the molded rubber sleeve is greater than the thickness of the second special-shaped block and smaller than the sum of the thicknesses of the first special-shaped block and the second special-shaped block; the shape of the outer side surface is matched with the shape of the inner cavity chamber for forming the rocket engine grain, and the end surface of the other end is matched with the positioning transition ring.
Furthermore, the molded rubber sleeve is provided with a fracture along the radial direction.
The invention also relates to a method for forming the rocket engine grain by adopting the structure, which comprises the following steps: firstly, mounting a formed rubber sleeve in place in an inner cavity of a shell of the rocket engine, then respectively mounting a first special-shaped block and a second special-shaped block to form a special-shaped assembly, mounting the special-shaped assembly in place, mounting a positioning transition ring until the special-shaped assembly is assembled in place, and then carrying out explosive loading pouring and explosive column forming; when the rocket engine explosive column is disassembled, other assembling and positioning transition rings are taken out firstly, then the formed rubber sleeve is taken out, and finally the first special-shaped block and the second special-shaped block are taken out in sequence to complete the rocket engine explosive column forming.
Further, a sponge sheet is arranged on the outer side of the special-shaped assembly and the inner layer of the heat-insulating layer of the powder charging cavity before powder charging, and after powder charging is finished, the sponge sheet is taken out after the combined core mold structure is disassembled.
The invention has the following beneficial effects:
1. the special-shaped component is divided into different special-shaped blocks along the circumferential direction, and the first special-shaped block contacts the explosive column to be formed and adopts a metal piece; the second abnormal shape piece is located the one side that the powder column was kept away from to first abnormal shape piece, and the second abnormal shape piece is the silicon rubber material, and first abnormal shape piece can satisfy the fashioned requirement of powder column, and second abnormal shape piece adopts the silicon rubber material, has certain flexibility, the later stage drawing of patterns of being convenient for. And set up the location step between first abnormal shape piece and second abnormal shape piece for first abnormal shape piece and second abnormal shape piece do not adopt fastening connection spare can connect the location, save the fastener operating space.
2. The first special-shaped block is provided with a positioning pin and a threaded hole on the end face close to the positioning transition ring side, and the positioning transition ring is provided with a positioning hole corresponding to the positioning pin and a bolt matched with the threaded hole on the end face close to the first special-shaped block. The first special-shaped block is connected and positioned with the positioning transition ring through the matching of the positioning pin and the positioning hole and the matching of the threaded hole and the bolt. The second special-shaped block is positioned through the positioning transition ring after passing through the formed rubber sleeve, and the structure is stable.
3. The formed rubber sleeve is integrally pressed and formed by silicon rubber, and the silicon rubber is a high-elasticity polymer with reversible deformation, can generate large deformation under the action of external force, can recover the original shape after the external force is removed, and has good physical properties. Adopt this shaping rubber sleeve can be fine for structure assembly and filling the space between inner chamber and the heterotypic subassembly in the powder charge process. The formed rubber sleeve is designed into an annular structure, is not convenient to install and disassemble, is easy to be occluded with other parts of the explosive column, and is difficult to install and disassemble mainly due to small size and small bending curvature radius through research by an inventor.
4. In order to prevent the problems that the demoulding force is increased and the disassembly difficulty is increased after the medicine is infiltrated between the special-shaped block and the heat insulation sleeve, the invention artificially reduces the clearance between the special-shaped assembly and the heat insulation sleeve, a certain inclined plane is additionally arranged on the positioning transition ring, and a certain tensioning force is generated when the special-shaped block is installed so as to reduce the clearance between the special-shaped assembly and the heat insulation sleeve. The design consideration of the inclined plane is the key point of ensuring that the slurry does not seep into the heat insulation sleeve after the inclined plane is added, and the structure of the sealing groove cannot be adopted due to the fact that the size of the structural part is too small; through processing the inclined plane on the location transition ring, the maximum thickness difference is less than 0.2mm, can avoid appearing oozing the medicine.
Drawings
Fig. 1 is a three-dimensional structure diagram of a special-shaped grain in the background art.
Fig. 2 is an exploded view of the composite mandrel structure of the present invention.
Fig. 3 is a cross-sectional view of the combined core mold structure of the present invention.
FIG. 4 is a view showing a state of use of the rocket motor in forming a grain using the structure of the present invention.
Detailed Description
The invention is further illustrated by the following examples, but the scope of the invention as claimed is not limited to the scope of the examples.
As shown in fig. 1-4, a combined core mold structure for rocket engine grain forming, a plurality of special-shaped gaps are arranged on the side surface of the grain, the structure comprises a plurality of groups of special-shaped assemblies, the groups of special-shaped assemblies and the grain special-shaped gaps are matched to form a cylinder, each group of special-shaped block assemblies are circumferentially provided with a first special-shaped block 1 and a second special-shaped block 2, and the first special-shaped block contacts with the grain to be formed and is a metal piece; the second special-shaped block is positioned on one side of the first special-shaped block, which is far away from the grain, and is made of silicon rubber, and the size of the thickest part of the first special-shaped block is smaller than the minimum size of a demoulding opening in rocket engine grain forming; the structure further comprises a molded rubber sleeve 3 and a positioning transition ring 4, wherein the end face of the molded rubber sleeve is clamped on the end face of the second special-shaped block, and the end face of the positioning transition ring is clamped on the end face of the first special-shaped block and the molded rubber sleeve.
In the preferred scheme, a positioning step 5 is arranged on the side, close to the second special-shaped block, of the first special-shaped block, a positioning groove 6 is arranged on the side, close to the first special-shaped block, of the second special-shaped block, and the positioning step is connected with the positioning groove in a matched mode. The positioning steps and the positioning grooves are axially arranged, the first special-shaped block is conveniently separated by the second special-shaped block, the positioning steps and the positioning grooves are matched and clamped, other fasteners are avoided being used, and the mounting and dismounting are convenient.
Further preferably, a double-sided adhesive layer is further arranged on the surface of the first special-shaped block, which is in contact with the second special-shaped block. The thickness of the double-sided adhesive layer is 0.1 mm. When being convenient for the mould assembly, first abnormal shape piece and second abnormal shape piece between fixed, drop when preventing the assembly.
In another preferred scheme, the end face of the first special-shaped block close to the positioning transition ring side is provided with a positioning pin 7 and a threaded hole 8, and the end face of the positioning transition ring close to the first special-shaped block is provided with a positioning hole corresponding to the positioning pin and a bolt 9 matched with the threaded hole. Further preferably, the end of the first profile block is provided with two positioning pins and 1 threaded hole, and the threaded hole is located between the two positioning pins. Through this setting, be convenient for first profile block and the location of location transition ring be connected.
Further preferably, the positioning transition ring is of a slope structure close to the first profile block end, and the thickness of the end part gradually increases from the center of the positioning transition ring to the outer side. Through the inclined plane setting, can prevent to increase drawing of patterns power because ooze the medicine between profile block and the adiabatic cover, reduce and dismantle the degree of difficulty.
In another preferred scheme, the thickness of the second profile block is gradually reduced from the end close to the molded rubber sleeve to the end far away from the molded rubber sleeve. The demoulding of the second special-shaped block is convenient.
Further preferably, the molded rubber sleeve is of an annular structure, and the width of one end face of the molded rubber sleeve is greater than the thickness of the second special-shaped block and smaller than the sum of the thicknesses of the first special-shaped block and the second special-shaped block; the shape of the outer side surface is matched with the shape of the inner cavity chamber for forming the rocket engine grain, and the end surface of the other end is matched with the positioning transition ring. The formed rubber sleeve is integrally pressed and formed by silicon rubber, certain gaps are reserved at the radial and axial matching positions of the silicon rubber and the positioning transition ring due to certain deformation of the silicon rubber in a thermal environment, in a specific case, a gap of 0.25mm is reserved between the inner side wall of the formed rubber sleeve and the positioning transition ring, and a gap of 0.3mm is reserved between the end face of the formed rubber sleeve and the positioning transition ring.
Further preferably, the formed rubber sleeve is provided with a cut-off along the radial direction. The molded rubber sleeve is cut after being integrally pressed and molded, and the width of a cutting opening is 0.2 mm. The arrangement of the cutting opening is convenient for the installation of the formed rubber sleeve, and is particularly convenient for the removal of the formed rubber sleeve.
The method for forming the rocket engine grain by adopting the structure comprises the following steps: firstly, mounting a formed rubber sleeve in place in an inner cavity of a shell of the rocket engine, then respectively mounting a first special-shaped block and a second special-shaped block to form a special-shaped assembly, mounting the special-shaped assembly in place, mounting a positioning transition ring until the special-shaped assembly is assembled in place, and then carrying out explosive loading pouring and explosive column forming; when the rocket engine explosive column is disassembled, other assembling and positioning transition rings are taken out firstly, then the formed rubber sleeve is taken out, and finally the first special-shaped block and the second special-shaped block are taken out in sequence to complete the rocket engine explosive column forming.
In the preferred scheme, a sponge sheet is arranged on the outer side of the special-shaped assembly and the inner layer of the heat-insulating layer of the charging cavity before charging, and after charging is finished, the sponge sheet is taken out after the combined core mold structure is disassembled. The medicine leakage between the special-shaped component and the heat insulating layer is prevented.
During specific assembly, the positioning ring 10, the forming pressing sleeve 11 and the boiling ring 12 are conventional accessories in explosive column charging forming, and a convex hemispherical surface is arranged on the forming pressing sleeve close to the end face of the explosive column for forming the special-shaped explosive column. The positioning ring is detachably connected with the positioning transition ring, the other end of the forming pressing sleeve is connected with the boiling ring, and the slurry is poured through the boiling ring. And (5) removing the accessories and all parts of the combined core mold structure after the pouring slurry is solidified, and finishing the preparation and the forming of the explosive column.
According to the technical scheme, due to the use of the silicon rubber, the operation space of a tool is saved, the silicon rubber is well suitable for propellant charging of a small-inner-hole explosive type engine, and the silicon rubber has the advantages of high assembly efficiency, stable quality and good reliability. At present, 2000 rocket engines are assembled, the size of a die cavity can meet various technical indexes of design, and multiple ground tests and flight test trials are carried out.
Claims (10)
1. The utility model provides a be used for fashioned combination mandrel structure of rocket engine grain, be equipped with a plurality of abnormal shape breachs on the grain side, its characterized in that: the structure comprises a plurality of groups of special-shaped assemblies, wherein the plurality of groups of special-shaped assemblies are matched with the special-shaped gaps of the explosive column to form a cylinder, each group of special-shaped block assemblies are annularly provided with a first special-shaped block (1) and a second special-shaped block (2), and the first special-shaped block is in contact with the explosive column to be formed and is a metal piece; the second special-shaped block is positioned on one side of the first special-shaped block, which is far away from the grain, and is made of silicon rubber, and the size of the thickest part of the first special-shaped block is smaller than the minimum size of a demoulding opening in rocket engine grain forming; the structure further comprises a molded rubber sleeve (3) and a positioning transition ring (4), the end face of the molded rubber sleeve clamps the end face of the second special-shaped block, and the end face of the positioning transition ring clamps the end face of the first special-shaped block and the molded rubber sleeve.
2. The structure of claim 1, wherein: the first special-shaped block is provided with a positioning step (5) close to the second special-shaped block, the second special-shaped block is provided with a positioning groove (6) close to the first special-shaped block, and the positioning step is connected with the positioning groove in a matched mode.
3. The structure of claim 2, wherein: and a double-sided adhesive layer is also arranged on the contact surface of the first special-shaped block and the second special-shaped block.
4. The structure of claim 1, wherein: the end face, close to the positioning transition ring side, of the first special-shaped block is provided with a positioning pin (7) and a threaded hole (8), and the end face, close to the first special-shaped block, of the positioning transition ring is provided with a positioning hole corresponding to the positioning pin and a bolt (9) matched with the threaded hole.
5. The structure of claim 4, wherein: the positioning transition ring is of an inclined surface structure close to the first special-shaped block end, and the thickness of the inclined surface structure gradually increases from the center of the positioning transition ring to the outer side.
6. The structure of claim 1, wherein: the second special-shaped block is gradually reduced in thickness from one end close to the formed rubber sleeve to one end far away from the formed rubber sleeve.
7. The structure of any one of claims 1-6, wherein: the width of one end face of the molded rubber sleeve is larger than the thickness of the second special-shaped block and smaller than the sum of the thicknesses of the first special-shaped block and the second special-shaped block; the shape of the outer side surface is matched with the shape of the inner cavity chamber for forming the rocket engine grain, and the end surface of the other end is matched with the positioning transition ring.
8. The structure of claim 7, wherein: the molded rubber sleeve is provided with a fracture along the radial direction.
9. A method of forming a rocket motor charge using the structure of any one of claims 1-8, comprising the steps of: firstly, mounting a formed rubber sleeve in place in an inner cavity of a shell of the rocket engine, then respectively mounting a first special-shaped block and a second special-shaped block to form a special-shaped assembly, mounting the special-shaped assembly in place, mounting a positioning transition ring until the special-shaped assembly is assembled in place, and then carrying out explosive loading pouring and explosive column forming; when the rocket engine explosive column is disassembled, other assembling and positioning transition rings are taken out firstly, then the formed rubber sleeve is taken out, and finally the first special-shaped block and the second special-shaped block are taken out in sequence to complete the rocket engine explosive column forming.
10. The method of claim 9, wherein: sponge pieces are arranged on the outer side of the special-shaped assembly and the inner layer of the heat-insulating layer of the charging cavity before charging, and after charging is finished, the sponge pieces are taken out after the combined core mold structure is disassembled.
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| CN201910825359.5A CN110566366B (en) | 2019-09-02 | 2019-09-02 | Combined core mold structure for rocket engine grain molding and use method thereof |
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| CN201910825359.5A CN110566366B (en) | 2019-09-02 | 2019-09-02 | Combined core mold structure for rocket engine grain molding and use method thereof |
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| CN110566366A CN110566366A (en) | 2019-12-13 |
| CN110566366B true CN110566366B (en) | 2021-07-13 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2749707B2 (en) * | 1990-06-01 | 1998-05-13 | ダイセル化学工業株式会社 | Two-stage thrust solid rocket motor |
| CN201227673Y (en) * | 2008-01-31 | 2009-04-29 | 西北工业大学 | Shell partition mould convenient to demoulding |
| CN102091736A (en) * | 2010-11-04 | 2011-06-15 | 西北工业大学 | Core mold for spinning and forming large-size complex curved generatrix thin-wall member with transverse inner ribs |
| CN105840344A (en) * | 2016-04-20 | 2016-08-10 | 哈尔滨工业大学 | Preparation and safe quick demolding process for solid rocket engine inner hole burning grain |
| CN106640422A (en) * | 2016-12-29 | 2017-05-10 | 内蒙古航天红峡化工有限公司 | Demoulding device for large-sized solid rocket engine mandrel wing |
| CN107420222A (en) * | 2017-08-21 | 2017-12-01 | 湖北三江航天江河化工科技有限公司 | A kind of powder charge core |
| CN208669458U (en) * | 2018-12-19 | 2019-03-29 | 西安黑曼巴防务科技有限公司 | A kind of solid propellant rocket pours medicine tooling and solid rocket motor grain |
-
2019
- 2019-09-02 CN CN201910825359.5A patent/CN110566366B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2749707B2 (en) * | 1990-06-01 | 1998-05-13 | ダイセル化学工業株式会社 | Two-stage thrust solid rocket motor |
| CN201227673Y (en) * | 2008-01-31 | 2009-04-29 | 西北工业大学 | Shell partition mould convenient to demoulding |
| CN102091736A (en) * | 2010-11-04 | 2011-06-15 | 西北工业大学 | Core mold for spinning and forming large-size complex curved generatrix thin-wall member with transverse inner ribs |
| CN105840344A (en) * | 2016-04-20 | 2016-08-10 | 哈尔滨工业大学 | Preparation and safe quick demolding process for solid rocket engine inner hole burning grain |
| CN106640422A (en) * | 2016-12-29 | 2017-05-10 | 内蒙古航天红峡化工有限公司 | Demoulding device for large-sized solid rocket engine mandrel wing |
| CN107420222A (en) * | 2017-08-21 | 2017-12-01 | 湖北三江航天江河化工科技有限公司 | A kind of powder charge core |
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