CN116787655A - Sand core mould structure of shell of sectional weight-reducing solid rocket engine - Google Patents
Sand core mould structure of shell of sectional weight-reducing solid rocket engine Download PDFInfo
- Publication number
- CN116787655A CN116787655A CN202211137786.2A CN202211137786A CN116787655A CN 116787655 A CN116787655 A CN 116787655A CN 202211137786 A CN202211137786 A CN 202211137786A CN 116787655 A CN116787655 A CN 116787655A
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- Prior art keywords
- weight
- section
- reducing pipe
- positioning
- end socket
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- Pending
Links
- 239000007787 solid Substances 0.000 title claims abstract description 24
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical group O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 36
- 208000016261 weight loss Diseases 0.000 claims description 17
- 238000007789 sealing Methods 0.000 claims description 10
- 230000006978 adaptation Effects 0.000 claims description 5
- 239000006004 Quartz sand Substances 0.000 claims description 4
- 230000017525 heat dissipation Effects 0.000 claims description 4
- 230000004580 weight loss Effects 0.000 claims 6
- 230000011218 segmentation Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 230000007547 defect Effects 0.000 abstract description 4
- 239000011257 shell material Substances 0.000 description 12
- 239000013585 weight reducing agent Substances 0.000 description 11
- 238000010586 diagram Methods 0.000 description 5
- 238000004804 winding Methods 0.000 description 5
- 238000004088 simulation Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 239000004372 Polyvinyl alcohol Substances 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 229910052602 gypsum Inorganic materials 0.000 description 1
- 239000010440 gypsum Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229920002451 polyvinyl alcohol Polymers 0.000 description 1
- 239000004576 sand Substances 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/76—Cores
-
- 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
- B29C70/32—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 on a rotating mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/748—Machines or parts thereof not otherwise provided for
- B29L2031/749—Motors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention discloses a sectional weight-reducing solid rocket engine shell sand core mould structure, which comprises a cylinder body section mould, wherein two ends of the cylinder body section mould are fixedly provided with two end socket section moulds which are oppositely arranged; the end socket section mould comprises an end socket female die, an end socket positioning shaft sleeve, an end socket weight-reducing pipe and an end socket weight-reducing pipe positioning disc; the cylinder section die comprises a cylinder section female die, a cylinder section female die base, a cylinder section lower weight-reducing pipe positioning disk, a cylinder section positioning shaft sleeve, a cylinder section weight-reducing pipe and a cylinder section upper weight-reducing pipe positioning disk; compared with the prior art, the invention solves the defect of heavier sand core quality and brings great convenience for processing and assembly; the core quality is lighter, can rationally reduce the diameter of dabber, be convenient for little polar hole casing's structural design and manufacturing.
Description
Technical Field
The invention relates to the field of rocket engine shell sand core molds, in particular to a segmented weight-reducing solid rocket engine shell sand core mold structure.
Background
With the day-to-day and month-to-day variation of aerospace technology, solid rocket engines are increasingly being developed towards high speed, high precision and small mass. The shell structure quality of the solid rocket engine is the most main negative quality of the engine, and the shell material with high strength and light weight is selected, so that the performance of the engine can be effectively improved.
The composite material has higher specific strength, specific rigidity, high temperature resistance and other performances, and the structure of the composite material can be designed according to the working requirements. The core mold is used as the basis of the winding process design, and the structure of the core mold directly influences the subsequent winding, curing and demolding, so that the structural design of the core mold is particularly important. When manufacturing resin-based composite products, a metal material is usually selected as a mold material, and for some special-shaped composite products with complex structures, a plurality of blocks are generally combined, but the difficulty of production and manufacturing is certainly increased. In recent years, a water-soluble core mold and a breakable core mold (mainly a gypsum core mold) have been sequentially pushed out for solid rocket motor cases, but in the case of solid rocket motor cases having a large aspect ratio, a small opening, and a large size, even in the case of water-soluble core mold, inconvenience is brought to the production of solid rocket motor cases during the processes of curing the core mold, winding fibers, and the like. Meanwhile, the heavy sand core quality and the low strength have great influence on the manufacturing precision of the solid rocket engine shell.
Disclosure of Invention
Aiming at the technical defects, the invention aims to provide a segmented weight-reduction solid rocket motor shell sand core mould structure, which solves the defects of large mass, long curing time, slow heat dissipation and the like of a solid rocket motor shell sand core mould.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention provides a sectional weight-reducing solid rocket engine shell sand core mould structure, which comprises a cylinder section mould, wherein two ends of the cylinder section mould are fixedly provided with two end socket section moulds which are oppositely arranged; the cylinder body section die and the end socket section die are coaxially arranged, and a through hole which is convenient for the die to be disassembled is formed in the axis of the cylinder body section die and the end socket section die;
the end socket section die comprises an end socket female die, the side surface of the inner cavity of the end socket female die is a front end socket molded surface of a solid rocket engine shell, the bottom surface of the inner cavity of the end socket female die is a joint bottom molded surface and is fixedly provided with an end socket positioning shaft sleeve, the upper end of the end socket positioning shaft sleeve is fixedly provided with an end socket weight-reducing pipe positioning disc, and a plurality of end socket weight-reducing pipes uniformly distributed in an annular array around the axis of the end socket weight-reducing pipe positioning disc are embedded in the end socket weight-reducing pipe positioning disc;
the barrel section mould includes a barrel section die, both ends are respectively with two head section mould fixed connection about the barrel section die, the sealed fixed barrel section die base of lower extreme of barrel section die, the fixed barrel section lower weight-reducing tube positioning disk of up end of barrel section die base, the fixed barrel section location axle sleeve in barrel section lower weight-reducing tube positioning disk middle part, weight-reducing tube positioning disk on barrel section location axle sleeve upper end fixed barrel section, barrel section weight-reducing tube positioning disk upper end still imbeds a plurality of barrel section weight-reducing tubes with head weight-reducing tube adaptation, barrel section weight-reducing tube upper end imbeds in the weight-reducing tube positioning disk on the barrel section.
Preferably, the middle part of the bottom surface of the inner cavity of the seal head female die and the middle part of the bottom surface of the seal head weight-reducing pipe positioning disc are respectively provided with a bulge, two ends of the seal head positioning shaft sleeve are respectively nested on and fixed with the two bulges, and the through holes are formed in the axes of the two bulges;
the middle part of the upper end of the lower weight-reducing pipe locating disc of the cylinder section and the middle part of the bottom surface of the upper weight-reducing pipe locating disc of the cylinder section are respectively provided with a cylindrical boss matched with the cylinder section locating shaft sleeve, the two ends of the cylinder section locating shaft sleeve are respectively nested on the cylindrical bosses and fixedly connected with the cylindrical bosses, and the through holes are formed in the axes of the two second protrusions.
Preferably, a through key slot is reserved in the seal head positioning shaft sleeve and matched with a key on the shaft for circumferential fixation of the sand core; the boss at the bottom of the seal head weight-reducing pipe positioning disc is matched with the seal head positioning shaft sleeve and used for axial positioning between dies;
the barrel section positioning shaft sleeve is used for positioning the lower weight-reducing pipe positioning disc of the barrel section and the upper weight-reducing pipe positioning disc of the barrel section, and a through key slot is reserved in the barrel section positioning shaft sleeve and is matched with an on-shaft key for circumferential fixation of the sand core.
Preferably, the cylinder section female die comprises two half cylinder section female dies which are spliced together;
the cylinder section die base circumference is equipped with the protruding with two half cylinder section die complex hollow cylinder section, half cylinder section die is fixed on the bellied outer wall of hollow cylinder section, the outer wall of section lower weight-reducing pipe positioning disk and the protruding inner wall looks adaptation of hollow cylinder section.
Preferably, the sealing head weight-reducing pipe positioning disc is provided with a plurality of positioning holes which are uniformly distributed around the axis of the sealing head weight-reducing pipe positioning disc in an annular array, and the sealing head weight-reducing pipe is placed in each positioning hole for positioning;
the lower weight-reducing pipe positioning disc and the barrel section upper weight-reducing pipe positioning disc are provided with a plurality of second positioning holes which are uniformly distributed in an annular array around the axis of the lower weight-reducing pipe positioning disc, and the barrel section weight-reducing pipes are placed in the second positioning holes for positioning.
Preferably, the end socket weight-reducing pipe and the barrel section weight-reducing pipe are both cylinders and are used for reducing the use amount of quartz sand.
Preferably, the seal head female die is of an axisymmetric structure, and the outer surface of the seal head female die is a cylindrical surface, so that uniform heat dissipation is ensured when the sand core is solidified and formed; the two half-cylinder section female dies form a cylinder, the shape of the cylinder is mutually matched with the seal head female dies
The invention has the beneficial effects that:
1. compared with the prior art, the invention solves the defect of heavier sand core quality and brings great convenience for processing and assembly; the core quality is lighter, can rationally reduce the diameter of dabber, be convenient for little polar hole casing's structural design and manufacturing.
2. The invention can not only reduce the material consumption, but also reduce the bearing requirement on the winding machine and shorten the curing time.
3. Compared with the prior art, the design of the weight-reducing pipe can volatilize water better, shorten the curing time of the sand core mould and reduce the usage amount of quartz sand.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic outline view of a seal head segment mold according to an embodiment of the present invention;
fig. 2 is a schematic diagram of an internal structure of a seal head segment mold according to an embodiment of the present invention;
FIG. 3 is a schematic view of the profile of a barrel section mold provided by an embodiment of the present invention;
FIG. 4 is a schematic view of the internal structure of a barrel section mold according to an embodiment of the present invention;
fig. 5 is a schematic diagram of the appearance of a seal head sand core mold (after weight reduction) according to an embodiment of the present invention;
fig. 6 is a schematic diagram of an internal structure of a seal head sand core mold (after weight reduction) according to an embodiment of the present invention;
fig. 7 is a schematic view of the outer shape of a sand core mold of a barrel (after weight reduction) according to an embodiment of the present invention;
fig. 8 is a schematic diagram of the internal structure of a sand core mold of a barrel (after weight reduction) according to an embodiment of the present invention.
Fig. 9 is a schematic diagram of an internal structure (not reducing weight) of a seal head sand core mold according to an embodiment of the invention.
Fig. 10 is a schematic view of the internal structure of a sand core mold of a barrel (without weight reduction) according to an embodiment of the present invention.
Fig. 11 is a structural simulation intensity calculation result provided in the embodiment of the present invention.
Reference numerals illustrate:
1-a seal head female die, 2-a seal head positioning shaft sleeve, 3-a seal head weight reducing disc and 4-a seal head weight reducing tube positioning disc; the device comprises a 5-barrel section die base, a 6-barrel section lower weight-reducing tube positioning disk, a 7-barrel section die, an 8-barrel section upper weight-reducing tube positioning disk, a 9-barrel section positioning shaft sleeve and a 10-barrel section weight-reducing tube.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 to 8, the sand core mould structure of the shell of the segmented weight-reducing solid rocket engine comprises: the cylinder body section mould and the end socket section moulds at the two ends are divided into a front end socket section mould and a rear end socket section mould according to the front-back sequence, and the two end socket section moulds have the same structure;
the head section mold comprises: the sealing head die 1, the sealing head positioning shaft sleeve 2, the sealing head weight-reducing pipe 3 and the sealing head weight-reducing pipe positioning disk 4; the barrel section die comprises: the device comprises a barrel section female die 7, a barrel section female die base 5, a barrel section lower weight-reducing pipe positioning disk 6, a barrel section positioning shaft sleeve 9, a barrel section weight-reducing pipe 10 and a barrel section upper weight-reducing pipe positioning disk 8;
the end socket female die 1 is of an axisymmetric structure, the outer surface of the end socket female die is a cylindrical surface, when a sand core is solidified and molded, uniform heat dissipation is ensured, the side surface of the inner surface is a front end socket molded surface of a solid rocket engine shell, a sand core machining allowance surface with a certain height is reserved, the bottom of the inner surface is a joint bottom molded surface, and a boss is reserved for fixing a die by matching with the end socket positioning shaft sleeve 2; the two ends of the end socket positioning shaft sleeve 2 are respectively matched with bulges arranged on the end socket female die 1 and the end socket weight-reducing pipe positioning disc 4 and are fixed together by screws;
the end socket positioning shaft sleeve 2 is used for positioning the end socket female die 1 and the end socket weight-reducing pipe positioning disc 4, a through key slot is reserved in the end socket female die and the end socket weight-reducing pipe positioning disc, and the end socket female die and the end socket weight-reducing pipe positioning disc are matched with a key on a shaft for circumferential fixation of a sand core; the boss at the bottom of the seal head weight-reducing pipe positioning disc 4 is matched with the seal head positioning shaft sleeve 2 and used for axial positioning between dies, and the positioning holes on the seal head weight-reducing pipe positioning disc 4 are used for fixing the seal head weight-reducing pipe 3; the end socket weight-reducing pipe 3 consists of a head part and a rod part, wherein the head part is a large flat cylindrical cake, the tail part is a thin long cylindrical rod, and the thin long cylindrical rod is matched with a positioning hole of the end socket weight-reducing pipe positioning disc 4.
The barrel section die comprises: the device comprises a barrel section female die 7, a barrel section female die base 5, a barrel section lower weight-reducing pipe positioning disk 6, a barrel section positioning shaft sleeve 9, a barrel section weight-reducing pipe 10 and a barrel section upper weight-reducing pipe positioning disk 8;
the cylinder section female die base 5 is matched with the two half cylinder section female dies 7, and the two cylinder section female dies 7 are fixed by bolts and nuts; the lower weight-reducing tube positioning disk 6 of the cylinder section is matched with the female die bases 5 of the two cylinder sections;
the cylinder section female die 7 is formed by splicing two identical half cylinder section female dies, a semi-cylinder shape is formed, a convex connecting plate is arranged at the contact surface part of the two half cylinder section female dies, through holes are drilled on the connecting plate and used for fixing the two half cylinder section female dies by bolts and nuts, and three hoisting ring threaded holes are respectively arranged at the upper end surfaces of the half cylinder section female dies and used for hoisting;
the cylinder section female die base 5 is provided with a hollow cylinder bulge with a small height, the outer surface of the cylinder section female die base is matched with the inner surface of the cylinder section female die 7, and the center of the circle is provided with a through hole, so that the die can be conveniently disassembled; the lower weight-reducing tube positioning disk 6 of the tube section is coaxially matched with the tube section female die base 5, a cylindrical boss is arranged in the middle of the lower weight-reducing tube positioning disk and is used for being matched with the tube section positioning shaft sleeve 9, and four positioning holes of the tube section weight-reducing tube 10 are formed in the periphery of the lower weight-reducing tube positioning disk; the barrel section positioning shaft sleeve 9 is used for positioning the barrel section lower weight-reducing pipe positioning disc 6 and the barrel section upper weight-reducing pipe positioning disc 8, and a through key slot is reserved in the barrel section positioning shaft sleeve and matched with an on-shaft key for circumferential fixation of the sand core; a hollow cylindrical boss is arranged in the middle of the weight-reducing pipe positioning disk 8 on the cylinder section and is used for being matched with the cylinder section positioning shaft sleeve 9, and four positioning holes of the positioning disk of the cylinder section weight-reducing pipe 10 are formed in the periphery of the cylinder section positioning shaft sleeve; the cylinder section weight-reducing pipe 10 is a cylinder and is matched with the second positioning hole of the cylinder section upper weight-reducing pipe positioning disk 8 and the second positioning hole of the cylinder section lower weight-reducing pipe positioning disk 6 for reducing the usage amount of quartz sand.
Examples; the length of the cylinder is 558mm, the radius is 146.2mm, the radius of the core shaft of the cylinder is 28.5mm, the ellipsoidal ratio is 1.7, and the radius of the core shaft of the front seal head and the rear seal head is 8.5mm. The proportion of the sand core mould is sand: water: polyvinyl alcohol = 25:3: the ultimate compression strength of the 1 sand core mould is 27MPa.
Referring to fig. 9-10, which are graphs of non-weight-reduction results in the prior art, referring to the following table, the weight reduction of the sand core mold of the present invention is 28.3% by comparing the mass before weight reduction and the mass after weight reduction, so that not only can the material consumption be reduced, but also the load-bearing requirement on the winding machine can be reduced, and the curing time can be shorter, referring to the weight reduction comparison in the following table:
the result of the structural simulation intensity calculation of the present invention is shown in fig. 11; according to the actual use condition, the simulation load is gravity acceleration, the simulation result strength is 21Mpa, which is lower than the allowable strength of the sand core mould, the sand core mould structure is not damaged, and the design strength requirement is met.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (7)
1. The utility model provides a segmentation subtracts heavy solid rocket engine casing psammitolite mould structure which characterized in that: the device comprises a barrel section mould, wherein two ends of the barrel section mould are fixedly provided with two end socket section moulds which are oppositely arranged; the cylinder body section die and the end socket section die are coaxially arranged, and a through hole which is convenient for the die to be disassembled is formed in the axis of the cylinder body section die and the end socket section die;
the end socket section die comprises an end socket female die (1), the side surface of the inner cavity of the end socket female die (1) is a front end socket molded surface of a solid rocket engine shell, the bottom surface of the inner cavity of the end socket female die is a joint bottom molded surface and is fixedly provided with an end socket positioning shaft sleeve (2), the upper end of the end socket positioning shaft sleeve (2) is fixedly provided with an end socket weight-reducing pipe positioning disc (4), and a plurality of end socket weight-reducing pipes (3) which are uniformly distributed in an annular array around the axis of the end socket weight-reducing pipe positioning disc (4) are embedded in the end socket weight-reducing pipe positioning disc;
the barrel section mould includes barrel section die (7), both ends respectively with two head section mould fixed connection about barrel section die (7), barrel section die base (5) are fixed in sealed lower extreme of barrel section die (7), weight-reducing pipe positioning disk (6) under the up end fixed barrel section of barrel section die base (5), weight-reducing pipe positioning disk (6) middle part fixed barrel section positioning shaft sleeve (9) under the barrel section, weight-reducing pipe positioning disk (8) on barrel section positioning shaft sleeve (9) upper end fixed barrel section, weight-reducing pipe positioning disk (6) upper end still imbeds a plurality of barrel section weight-reducing pipes (10) with head weight-reducing pipe (3) adaptation under the barrel section, in weight-reducing pipe positioning disk (8) on barrel section weight-reducing pipe (10) upper end embedding barrel section.
2. The segmented weight-loss solid rocket motor housing core mold structure of claim 1, wherein:
the middle part of the bottom surface of the inner cavity of the seal head female die (1) and the middle part of the bottom surface of the seal head weight-reducing pipe positioning disc (4) are respectively provided with a bulge, two ends of the seal head positioning shaft sleeve (2) are respectively nested on and fixed with the two bulges, and the through holes are formed in the axes of the two bulges;
the lower weight-reducing pipe locating disc (6) of section of a cylinder upper end middle part, section of a cylinder upper weight-reducing pipe locating disc (8) bottom surface middle part all are equipped with the cylinder boss with section of a cylinder locating shaft sleeve (9) adaptation, the both ends of section of a cylinder locating shaft sleeve (9) nest respectively on the cylinder boss and rather than fixed connection, the through-hole is seted up on two bellied axis of second.
3. The segmented weight-loss solid rocket motor housing core mold structure of claim 1, wherein:
a through key slot is reserved in the seal head positioning shaft sleeve (2) and matched with a key on the shaft for circumferential fixation of the sand core; the boss at the bottom of the seal head weight-reducing pipe positioning disc (4) is matched with the seal head positioning shaft sleeve (2) and used for axial positioning between dies;
the barrel section positioning shaft sleeve (9) is used for positioning a barrel section lower weight-reducing pipe positioning disc (6) and a barrel section upper weight-reducing pipe positioning disc (8), a through key slot is reserved in the barrel section positioning shaft sleeve, and the barrel section positioning shaft sleeve is matched with an on-shaft key for circumferential fixation of a sand core.
4. The segmented weight-loss solid rocket motor housing core mold structure of claim 1, wherein: the cylinder section female die (7) comprises two half cylinder section female dies which are spliced together;
the cylinder section die base (5) circumference is equipped with the protruding with two half cylinder section die complex hollow cylinder section, half cylinder section die is fixed on the bellied outer wall of hollow cylinder section, the outer wall of section lower weight-reducing pipe positioning disk (6) and the protruding inner wall looks adaptation of hollow cylinder section.
5. The segmented weight-loss solid rocket motor housing core mold structure of claim 1, wherein:
the sealing head weight-reducing pipe positioning disc (4) is provided with a plurality of positioning holes which are uniformly distributed around the axis of the sealing head weight-reducing pipe positioning disc in an annular array, and the sealing head weight-reducing pipe (3) is placed in each positioning hole for positioning;
the lower weight-reducing pipe positioning disc (6) and the barrel section upper weight-reducing pipe positioning disc (8) are provided with a plurality of second positioning holes which are uniformly distributed in an annular array around the axis of the lower weight-reducing pipe positioning disc, and the barrel section weight-reducing pipe (10) is placed in each second positioning hole for positioning.
6. The segmented weight-loss solid rocket motor housing core mold structure of claim 1, wherein: the end socket weight-reducing pipe (3) and the barrel section weight-reducing pipe (10) are both cylinders and are used for reducing the usage amount of quartz sand.
7. The segmented weight-loss solid rocket motor housing core mold structure of claim 1, wherein: the seal head female die (1) is of an axisymmetric structure, and the outer surface of the seal head female die is a cylindrical surface, so that uniform heat dissipation is ensured when the sand core is solidified and formed; the two half-cylinder section female dies (7) form a cylinder, and the shape of the cylinder is mutually matched with the seal head female die (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211137786.2A CN116787655A (en) | 2022-09-19 | 2022-09-19 | Sand core mould structure of shell of sectional weight-reducing solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211137786.2A CN116787655A (en) | 2022-09-19 | 2022-09-19 | Sand core mould structure of shell of sectional weight-reducing solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116787655A true CN116787655A (en) | 2023-09-22 |
Family
ID=88033503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211137786.2A Pending CN116787655A (en) | 2022-09-19 | 2022-09-19 | Sand core mould structure of shell of sectional weight-reducing solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116787655A (en) |
-
2022
- 2022-09-19 CN CN202211137786.2A patent/CN116787655A/en active Pending
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