CN111070518A - Solid rocket engine core insert heat insulation layer forming device and using method - Google Patents
Solid rocket engine core insert heat insulation layer forming device and using method Download PDFInfo
- Publication number
- CN111070518A CN111070518A CN201911200328.7A CN201911200328A CN111070518A CN 111070518 A CN111070518 A CN 111070518A CN 201911200328 A CN201911200328 A CN 201911200328A CN 111070518 A CN111070518 A CN 111070518A
- Authority
- CN
- China
- Prior art keywords
- mold core
- mold
- core
- insulation layer
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
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
- B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
- B29C39/02—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles
- B29C39/10—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles
-
- 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
- B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
- B29C39/22—Component parts, details or accessories; Auxiliary operations
Landscapes
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention provides a solid rocket engine core insert heat insulation layer forming device, which comprises a mold core (1), a mold core positioning plate (2), a positioning ring (3), a sealing base (4), a pressurizing mechanism (5), a first upper locking template (6), a second upper locking template (7) and a mold locking rod (8); the mold core (1) is a punch forming component made of low-viscosity insulating materials; the mold core positioning plate (2) is used for fixing the mold core (1); the positioning ring (3) is used for fixing the engine shell and is matched with the mold core positioning plate (2) to send the mold core (1) into the cavity of the engine shell; the sealing base (4) is used for sealing the bottom of the cavity of the engine shell and forming sealing; the pressurizing mechanism (5) is used for applying pressure to the mold core (1) to enable the mold core (1) to extrude the low-viscosity insulating material in the cavity of the engine shell; the first upper locking template (6), the second upper locking template (7) and the mold locking rod (8) are matched for use, and mold locking and pressure maintaining are carried out on the mold core (1) which is punched in place.
Description
Technical Field
The invention belongs to the field of manufacturing of a heat insulating layer of a solid rocket engine, and particularly relates to a solid rocket engine core insert heat insulating layer forming device and a using method.
Background
At present, materials of a heat insulation layer of a solid rocket engine are in a diversified development trend, and the traditional method for manufacturing the heat insulation layer of the solid rocket engine mainly comprises processes of patch air bag inner support pressurization, compression molding, heat insulation pipe body outer molding assembly and the like. The inner support of the air bag can not meet the precision of the size of the heat insulation pipe hole due to the flexible pressurizing characteristic; the compression molding process has the advantages of mature and stable technology, wide application range and the like, but has complex operation procedures and lower production efficiency, and has extremely high requirement on the precision of compression molding equipment, higher cost and low efficiency aiming at the engine shell with larger long diameter, high requirement on the dimensional precision and a special-shaped hole structure; for the external forming process, the assembly of the heat insulating layer and the shell can be realized only by requiring the simple structure of the engine shell, and the application range is narrow.
The modern operational environment has higher and higher requirements on the maneuvering performance of the solid rocket tactic missile, the structure of an engine presents a complicated trend, in order to meet the requirement of high-efficiency manufacture of a heat insulating layer, various heat insulating material professional research organizations successively provide low-viscosity paste heat insulating materials to realize a high-efficiency pressure propulsion molding heat insulating process, and for the low-viscosity heat insulating materials, the traditional air bag inner support pressurizing process, compression molding process and in-vitro molding process are difficult to meet the development requirement. Therefore, it is necessary to develop a stable, reliable and strong-implementability molding process to meet the requirement of batch production of high-performance missile weapons.
Disclosure of Invention
The invention provides a solid rocket engine core insert heat insulation layer forming device which can realize one-step forming in a low-viscosity heat insulation material solid rocket engine shell, obviously improve the precision and improve the heat insulation production efficiency of an engine.
The technical scheme of the invention is that the solid rocket engine core insert heat insulation layer forming device comprises a mold core, a mold core positioning plate, a positioning ring, a sealing base, a pressurizing mechanism, a first upper locking template, a second upper locking template and a mold locking rod; the die core is a punch forming component made of low-viscosity insulating materials, and the shape and the size of the outer surface of the die core are matched with the inner surface of the solid rocket motor core insertion heat insulation layer so as to ensure the shape and the size of the inner surface of the heat insulation layer; the mold core positioning plate is used for fixing the mold core and guiding the mold core to be sent into a cavity of the engine shell; the positioning ring is used for fixing the engine shell and is matched with the mold core positioning plate to send the mold core into the cavity of the engine shell through the hole on the surface of the positioning ring; the sealing base is used for plugging the bottom of the cavity of the engine shell and forming sealing, and comprises a sealing ring; the pressurizing mechanism is used for applying pressure to the mold core through the mold core positioning plate so that the mold core extrudes the low-viscosity insulating material in the cavity of the engine shell; first cope match-plate pattern, second cope match-plate pattern and mode locking pole cooperation are used, carry out the mode locking pressurize to the mold core after the punching is targetting in place, make by extruded low viscosity insulating material at the engine housing intracavity, first cope match-plate pattern sets up on the mold core locating plate, the setting of second cope match-plate pattern is under fixed engine housing bottom, the mode locking pole includes many, all connects to be fixed between first cope match-plate pattern, the second cope match-plate pattern.
Furthermore, the mold core is provided with a taper (big end up and small end down) of less than 0.5 degree along the stress direction of the mold core positioning plate within the allowable range of the size precision of the insulating layer, so as to be convenient for demolding and drawing.
Further, guide pillars are arranged on the periphery of the lower surface of the mold core positioning plate; and guide sleeves matched with the guide pillars on the mold core positioning plate in position are arranged around the positioning ring, and the circumferences of the guide sleeves are larger than those of the guide pillars so that the guide pillars enter the guide sleeves.
Furthermore, the coaxiality error of the guide post and the guide sleeve is less than 0.05 mm.
Furthermore, the mold core positioning plate is fixedly connected with the mold core through a threaded hole and a bolt.
Further, the pressurizing mechanism is a large engine or a portable jack so as to provide a mold clamping force of more than 5 MPa.
Furthermore, the upper die plate, the lower die plate and the die rod are connected through bolts to lock the die core and the cavity of the engine shell.
The invention also provides a solid rocket engine core insert heat insulation layer molding method, which uses the solid rocket engine core insert heat insulation layer molding device and comprises the following steps:
the method comprises the following steps: preparing a low-viscosity heat-insulating material, and weighing the low-viscosity heat-insulating material according to a theoretical weight for later use;
step two: the lower end of the engine shell is fixedly plugged through a sealing base and a sealing ring, and a positioning ring is fixed with the engine shell;
step three: connecting the mold core positioning plate with the mold core for later use;
step four: pouring a low-viscosity heat-insulating material into the cavity of the engine shell, hoisting a mold core positioning plate and a mold core through a special hoisting frame, and enabling a guide post to enter a guide sleeve of a positioning ring, so that the mold core is slowly inserted into the cavity of the engine shell through a hole in the center of the positioning ring, and is combined into the cavity of the engine shell to a certain height under the action of self weight;
step five: pressurizing the mold core positioning plate by a pressurizing mechanism to press the mold core in place, and locking and maintaining the pressure by the upper mold plate, the lower mold plate and the mold locking rod after the mold is closed in place;
step six: and (5) after the mold is locked, releasing the pressure, curing, and demolding after curing.
Further, the curing mode in the sixth step is room temperature curing or curing at a temperature in the range of 140-180 ℃.
Further, the low-viscosity heat insulating material in the first step can be a low-viscosity ethylene propylene diene monomer heat insulating layer, a low-viscosity resin molding compound and a low-viscosity silicon rubber material.
The invention provides a solid rocket engine core insert heat insulation layer forming device, which comprises a mold core, a guide post tool for fixing the mold core, a positioning ring guide sleeve tool, a lower sealing base, a pressurizing mechanism, an upper locking template, a lower locking template, a mold locking rod and other components, wherein the outer profile of the mold core is matched with the inner profile of the heat insulation layer to ensure the size of the inner profile of the heat insulation layer, and a taper angle below 0.5 degrees is set within an allowable range of size precision to facilitate demolding and drawing; the die core fixing tool comprises a guide post device, the guide post device is connected with a die core through a threaded hole and a bolt for use, the positioning ring and the guide sleeve mechanism are combined mechanisms, and the coaxiality error of the positioning ring and the guide sleeve mechanism is less than 0.05 mm; the lower sealing base is connected with the shell in a sealing way; the pressurizing mechanism provides mold core propelling pressure to pressurize a press machine (a large engine) or a portable jack (a small and medium engine), and finally the mold locking force is more than 5MPa to ensure that the mold cavity is fully filled with heat insulating materials, so that subsequent vulcanization is facilitated; after the mold core is pressed and matched in place, the upper and lower mold locking plates and the mold locking rods are connected through bolts to lock the mold core and the shell cavity, so that pressure maintaining is realized; the curing mode is room temperature curing or medium-high temperature curing (140-180 ℃); finally demoulding to obtain the integrated heat insulation shell. The device and the method finish the one-step molding of the solid rocket engine shell of the heat-insulating material, and improve the heat-insulating production efficiency of the engine.
Compared with the prior art, the invention has the following advantages:
(1) the production efficiency is high. Can rely on the mould core to insert the core pressure injection molding once according to the production demand, easy and simple to handle easily realizes batch production.
(2) The product size control precision is high. The mold core and the positioning mechanism ensure high precision of the molded surface and the size of the heat insulating layer.
(3) The application range is wide. The molding method can meet the molding requirements of the heat insulating layer with uniform thickness and the heat insulating layer with complicated structure such as variable thickness, irregular shape and the like.
(4) Compared with the air bag internal support pressurizing, compression molding and external forming process which are widely adopted at present, the production efficiency is improved, the product size control precision is improved, the capability of quickly manufacturing products is achieved, and the limitation of the prior art is made up.
Drawings
These and/or other aspects and advantages of the present invention will become more apparent and more readily appreciated from the following detailed description of the embodiments of the invention, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic diagram of the components and the overall structure of a solid rocket motor core insert insulation layer forming device according to an embodiment of the present invention when the mold core is not pressed in place, wherein the upper mold plate, the lower mold plate and the mold locking rods are not included;
fig. 2 is a schematic diagram of the components and the overall structure of the solid rocket motor core insert insulation layer forming device in the embodiment of the invention when the mold core is pressed in place.
Detailed Description
In order that those skilled in the art will better understand the present invention, the following detailed description of the invention is provided in conjunction with the accompanying drawings and the detailed description of the invention.
Example 1
A solid rocket engine lock pin heat insulation layer forming device is shown in figures 1 and 2, and comprises a mold core 1, a mold core positioning plate 2, a positioning ring 3, a sealing base 4, a pressurizing mechanism 5, a first upper locking template 6, a second upper locking template 7 and a mold locking rod 8; the mold core 1 is a punch forming component made of low-viscosity insulating materials, and the shape and the size of the outer surface of the punch forming component are matched with the inner surface of a solid rocket motor core insertion heat insulation layer so as to ensure the shape and the size of the inner surface of the heat insulation layer; the mold core positioning plate 2 is used for fixing the mold core 1 and guiding the mold core 1 to be sent into a cavity of the engine shell, and the mold core positioning plate 2 and the mold core 1 are fixedly connected through a threaded hole and a bolt; the positioning ring 3 is used for fixing the engine shell and is matched with the mold core positioning plate 2 to send the mold core 1 into the cavity of the engine shell through the hole on the surface of the positioning ring 3; the sealing base 4 is used for sealing the bottom of the cavity of the engine shell and forming sealing, and the sealing base 4 comprises a sealing ring; the pressurizing mechanism 5 is used for applying pressure to the mold core 1 through the mold core positioning plate 2 so that the mold core 1 extrudes the low-viscosity insulating material in the cavity of the engine shell, and the pressurizing mechanism 5 is a large-scale engine or a portable jack and is used for providing a mold locking force larger than 5MPa so that the low-viscosity insulating material is extruded and is cured and molded in the pressure state; first cope match-plate pattern 6, second cope match-plate pattern 7 and die-locking rod 8 cooperation are used, carry out the mode locking pressurize to die core 1 after the punching is targetting in place, make by extruded low viscosity insulating material at the engine housing intracavity, first cope match-plate pattern 6 sets up on die core locating plate 2, second cope match-plate pattern 7 sets up under fixed engine housing bottom, die-locking rod 8 includes many, all connects to fix between first cope match-plate pattern 6, second cope match-plate pattern 7, and preferably cope match-plate pattern 6, lower die-locking plate pattern 7 and die-locking rod 8 all pin die core 1 and engine housing chamber through bolted connection.
Preferably, the mold core 1 is provided with a taper (big end up and small end down) of less than 0.5 degrees along the stress direction of the mold core positioning plate 2 within the allowable range of the dimensional accuracy of the insulating layer, so as to facilitate demolding and drawing.
In order to enable the mold core 1 to vertically enter the cavity of the engine more smoothly, guide posts are arranged on the periphery of the lower surface of the mold core positioning plate 2; and guide sleeves matched with the guide pillars on the mold core positioning plate 2 in position are arranged around the positioning ring 3, the perimeter of each guide sleeve is larger than that of each guide pillar, so that each guide pillar enters the corresponding guide sleeve, and the coaxiality error between each guide pillar and each guide sleeve is smaller than 0.05 mm.
Example 2: preparation of heat insulating layer of secondary combustion chamber of solid rocket engine
The core insert injection of the engine shell is completed according to the following steps:
the method comprises the following steps: preparing a silicon resin/fiber heat-insulating material, and weighing the silicon resin/fiber heat-insulating material according to the theoretical weight for later use;
step two: the bottom of the engine is fixedly plugged through a sealing base (with a sealing ring), a casting end positioning ring (with a guide sleeve) is assembled with the engine shell, and the coaxiality tolerance of the guide pillar and the guide sleeve with a mold core is 0.03 mm;
step three: assembling the mold core and a mold core fixing plate (with a guide post) and the mold core for use, wherein the cone angle of the mold core is 0.4 degrees,
step four: and pouring the silicon resin/fiber heat-insulating material into the shell cavity, inverting the guide post into the guide sleeve through a special hoisting frame, slowly inserting the mold core into the mold cavity, and enabling the mold core to be fitted into the shell cavity under the action of self weight.
Step five: the mold core is pressurized in place through the external connecting plate and a 50T portable digital display jack, and the final equivalent pressure is 6 MPa.
Step six: after the upper and lower locking templates and the locking rods are used for locking, the outer connecting plate and the jack are disassembled, and then the product is placed into a drying room for curing, wherein the curing parameter is 160 ℃ and 4 hours.
Step seven: and demolding after curing is finished to finish heat insulation.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A solid rocket engine lock pin heat insulation layer forming device is characterized by comprising a mold core (1), a mold core positioning plate (2), a positioning ring (3), a sealing base (4), a pressurizing mechanism (5), a first upper locking template (6), a second upper locking template (7) and a mold locking rod (8);
the mold core (1) is a punch forming component made of low-viscosity insulating materials, and the shape and the size of the outer surface of the punch forming component are matched with the inner surface of the solid rocket engine core insert heat insulating layer so as to ensure the shape and the size of the inner surface of the heat insulating layer;
the mold core positioning plate (2) is used for fixing the mold core (1) and guiding the mold core (1) to be sent into a cavity of the engine shell;
the positioning ring (3) is used for fixing the engine shell and is matched with the mold core positioning plate (2) to send the mold core (1) into the cavity of the engine shell through the hole on the surface of the positioning ring (3);
the sealing base (4) is used for plugging the bottom of the cavity of the engine shell and forming sealing, and the sealing base (4) comprises a sealing ring;
the pressurizing mechanism (5) is used for applying pressure to the mold core (1) through the mold core positioning plate (2) so that the mold core (1) extrudes the low-viscosity insulating material in the cavity of the engine shell;
first cope match-plate pattern (6), second cope match-plate pattern (7) and mode locking pole (8) cooperation are used, carry out the mode locking pressurize to die core (1) after the punching in place, make by extruded low viscosity insulating material at the engine housing intracavity, first cope match-plate pattern (6) set up on die core locating plate (2), second cope match-plate pattern (7) set up under fixed engine housing bottom, mode locking pole (8) include many, all connect to fix between first cope match-plate pattern (6), second cope match-plate pattern (7).
2. The solid rocket motor core insert insulation layer forming device of claim 1, wherein the mold core (1) is provided with a taper with a size of less than 0.5 degrees at the upper part and the lower part along the stress direction of the mold core positioning plate (2) within the allowable range of the size precision of the motor core insert insulation layer, so as to facilitate the demolding and the drawing.
3. The solid rocket engine core insert insulation layer forming device according to claim 1, wherein guide posts are arranged around the lower surface of the core positioning plate (2); the periphery of the positioning ring (3) is provided with a guide sleeve matched with the guide pillar on the mold core positioning plate (2) in position, and the perimeter of the guide sleeve is larger than that of the guide pillar so that the guide pillar can enter the guide sleeve.
4. The solid rocket motor core insert insulation layer molding apparatus of claim 3, wherein the coaxiality error of the guide post and the guide sleeve is less than 0.05 mm.
5. The solid rocket engine core insert insulation layer forming device of claim 1, wherein the mold core positioning plate (2) and the mold core (1) are fixedly connected through a threaded hole and a bolt.
6. The solid rocket motor core insert insulation layer molding apparatus of claim 1, wherein the pressurizing mechanism (5) is a large motor or a portable jack to provide a clamping force of more than 5 MPa.
7. The apparatus for forming the thermal insulation layer of the core insert of the solid rocket motor according to claim 1, wherein the upper locking plate (6), the lower locking plate (7) and the locking rod (8) are all connected and locked with the core (1) and the cavity of the motor case through bolts.
8. A method of forming a solid rocket motor core insert insulation layer using the solid rocket motor core insert insulation layer forming device according to any one of claims 1 to 7, comprising the steps of:
the method comprises the following steps: preparing a low-viscosity heat-insulating material, and weighing the low-viscosity heat-insulating material according to a theoretical weight for later use;
step two: the lower end of the engine shell is fixedly plugged through a sealing base and a sealing ring, and a positioning ring (3) is fixed with the engine shell;
step three: connecting the mold core positioning plate (2) with the mold core (1) for later use;
step four: pouring a low-viscosity heat-insulating material into the cavity of the engine shell, hoisting a mold core positioning plate (2) and a mold core (1) by a special hoisting frame, and enabling a guide post to enter a guide sleeve of a positioning ring (3), so that the mold core (1) is slowly inserted into the cavity of the engine shell through a hole in the center of the positioning ring (3) and is combined into the cavity of the engine shell to a certain height under the action of self weight;
step five: pressurizing the mold core positioning plate (2) through a pressurizing mechanism (5) to press the mold core (1) in place, and locking and maintaining the pressure through an upper mold plate (6), a lower mold plate (7) and a mold locking rod (8) after the mold is closed in place;
step six: and (5) after the mold is locked, releasing the pressure, curing, and demolding after curing.
9. The method for forming a core insert thermal insulation layer of a solid rocket motor according to claim 8, wherein the curing in the sixth step is room temperature curing or curing at a temperature in the range of 140-180 ℃.
10. The method of claim 8, wherein the low viscosity insulation material of step one is one or more of a low viscosity ethylene propylene diene monomer rubber insulation layer, a low viscosity resin molding compound, and a low viscosity silicone rubber material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911200328.7A CN111070518A (en) | 2019-11-29 | 2019-11-29 | Solid rocket engine core insert heat insulation layer forming device and using method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911200328.7A CN111070518A (en) | 2019-11-29 | 2019-11-29 | Solid rocket engine core insert heat insulation layer forming device and using method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111070518A true CN111070518A (en) | 2020-04-28 |
Family
ID=70312082
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911200328.7A Pending CN111070518A (en) | 2019-11-29 | 2019-11-29 | Solid rocket engine core insert heat insulation layer forming device and using method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111070518A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112140526A (en) * | 2020-08-27 | 2020-12-29 | 西安近代化学研究所 | Forming device for preparing high-viscosity silicon-based heat insulation layer in variable-section thin-wall shell |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106827349A (en) * | 2015-12-07 | 2017-06-13 | 上海新力动力设备研究所 | A kind of heat insulation layer mould and method |
| CN207206866U (en) * | 2017-08-10 | 2018-04-10 | 无锡锦和科技有限公司 | A kind of auto-separating combination die of yielding rubber bearing |
-
2019
- 2019-11-29 CN CN201911200328.7A patent/CN111070518A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106827349A (en) * | 2015-12-07 | 2017-06-13 | 上海新力动力设备研究所 | A kind of heat insulation layer mould and method |
| CN207206866U (en) * | 2017-08-10 | 2018-04-10 | 无锡锦和科技有限公司 | A kind of auto-separating combination die of yielding rubber bearing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112140526A (en) * | 2020-08-27 | 2020-12-29 | 西安近代化学研究所 | Forming device for preparing high-viscosity silicon-based heat insulation layer in variable-section thin-wall shell |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8038923B2 (en) | Methods of forming a part using shape memory polymers | |
| CN107599319A (en) | A kind of rail dampener preparation method and primary and secondary structure automatic stripping die | |
| CN111070518A (en) | Solid rocket engine core insert heat insulation layer forming device and using method | |
| CN109130237B (en) | Manufacturing die and manufacturing method of integrally-formed carbon fiber propeller | |
| CN114951555B (en) | Tandem type water-soluble sand core mould and manufacturing method thereof | |
| CN108127939A (en) | Composite material female connector molding die | |
| CN114834062A (en) | Forming process of special-shaped airplane air inlet channel | |
| CN217512810U (en) | Water-soluble sand mandrel of serial-type | |
| CN208068934U (en) | Composite material female connector molding die | |
| CN114986806A (en) | Barrel-shaped polydicyclopentadiene hollow product mold and molding process | |
| CN108714994B (en) | Human body target production process with good filling effect | |
| CN214324062U (en) | Demoulding mechanism for injection mould | |
| CN103214847A (en) | Silicon rubber mold for integral moulding of composite skirt and preparation method | |
| CN202895554U (en) | Combined mold for composite jacket of arrester | |
| CN112008920A (en) | Core mold for producing rocket engine composite material shell and forming method thereof | |
| CN220113790U (en) | EPS blanking cover shaping tool structure | |
| CN112721044A (en) | Coil framework forming die | |
| CN220297694U (en) | Preforming die for high length-diameter ratio heat insulation coating sleeve | |
| CN116533438B (en) | Injection molding device and process for microphone plastic pipe | |
| CN213412693U (en) | Tool for paste heat-insulating material core insert injection process | |
| CN217729736U (en) | Forming device for thin-wall tubular special-shaped part | |
| CN220028601U (en) | One-step forming die for engine exhaust pipe | |
| CN220464818U (en) | Compression molding's unmanned aerial vehicle intake duct lip forming die | |
| CN219503690U (en) | Die casting die with split core-pulling structure | |
| CN216885305U (en) | Unmanned aerial vehicle motor cabinet one shot forming mould |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200428 |