CN202225363U - Integral compression molding mould for rocket shell ejecting pipe - Google Patents
Integral compression molding mould for rocket shell ejecting pipe Download PDFInfo
- Publication number
- CN202225363U CN202225363U CN201120361765XU CN201120361765U CN202225363U CN 202225363 U CN202225363 U CN 202225363U CN 201120361765X U CN201120361765X U CN 201120361765XU CN 201120361765 U CN201120361765 U CN 201120361765U CN 202225363 U CN202225363 U CN 202225363U
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- China
- Prior art keywords
- mould
- volution
- jet pipe
- patrix
- stopping ring
- 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.)
- Expired - Fee Related
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- 238000000748 compression moulding Methods 0.000 title claims abstract description 16
- 238000000034 method Methods 0.000 claims abstract description 8
- 230000000295 complement effect Effects 0.000 claims description 9
- 239000002184 metal Substances 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- 239000000463 material Substances 0.000 abstract description 5
- 230000006835 compression Effects 0.000 abstract 4
- 238000007906 compression Methods 0.000 abstract 4
- 238000000465 moulding Methods 0.000 abstract 1
- 238000012856 packing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
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Abstract
The utility model relates to an integral compression molding mould for a rocket shell ejecting pipe and belongs to the technical field of material forming in rocket processing. The integral compression molding mould comprises a lower mould plate, an outer mould, a lower mould, an inner mould, a thread ring, a stopping ring, a compression bolt, an upper mould and an upper mould plate, wherein the inner mould is composed of two components for forming a conical cylinder structure; the outer mould is sleeved outside the lower mould and is fixed with the lower mould plate; a metallic shell of the rocket shell ejecting pipe, the inner mould formed into a conical cylinder and the thread ring are placed into an inner cavity of the outer mould in sequence; the stopping ring is fixed at the upper end of the thread ring; the stopping ring is fixed with the lower mould plate through the compression bolt; an upper mould guiding hole is processed at the center of the stopping ring of an inner compression film; the upper mould is fixed at the lower end of the upper mould plate; and the upper end of the upper mould plate is connected with a pressure device. The integral compression molding mould provided by the utility model is simple in structure and convenient in de-molding; the integral compression for the rocket shell ejecting pipe is realized; the processing process and the processing period are reduced; the production efficiency is increased; and the consistency of the products is excellent.
Description
Technical field
The utility model relates to the whole compression molding forming mould of a kind of rocket projectile jet pipe, belongs to the arrow in-process stock forming technique field that plays.
Background technology
In the processing of hail-proof rain-increasing rocket; Often need some jet pipe compression moulding parts of processing; The jet pipe of this rocket projectile is dimerous by jet pipe leading portion and jet pipe back segment; Because jet pipe leading portion and jet pipe back segment are the structure of dehiscing in two ends, existing compacting tool set can't be realized the compacting of this infrastructure product.Traditional handicraft is the mode that adopts split compression moulding processing to the processing of the jet pipe of rocket projectile; Promptly add man-hour in compression moulding; After jet pipe leading portion and the compression moulding of jet pipe back segment difference; Respectively machine on the junction housing of jet pipe leading portion and jet pipe back segment is added screw thread then, screw the mode that forms through self screw thread again.This method manufacturing procedure is many, the process-cycle is long, utilization rate of electrical is low, production efficiency is low, homogeneity of product is poor and the product precision does not often reach designing requirement.
Summary of the invention
The purpose of the utility model is to adopt the split method for processing in order to solve traditional handicraft processing rocket projectile jet pipe; Problems such as manufacturing procedure is many, the process-cycle is long, production efficiency is low, homogeneity of product difference, and provide a kind of rocket projectile jet pipe whole compression molding forming mould.
The purpose of the utility model realizes through following technical scheme:
The whole compression molding forming mould of a kind of rocket projectile jet pipe of the utility model comprises lower bolster, external mold, counterdie, internal mold, volution, stopping ring, hold-down bolt, patrix, cope match-plate pattern;
The lower bolster upper surface is processed with stepped through hole, and the counterdie lower end is through stepped through hole and lower bolster screens, and the profile of counterdie upper end is consistent with the interior shape of rocket projectile jet pipe leading portion, and internal mold is for forming two bulk-breakings of awl barrel structure; Outer die casing is fixed with the lower bolster screw outside counterdie; Outer mold cavity is put into internal mold and the volution behind rocket projectile jet pipe metal shell, the composition awl tube successively; Internal mold and volution are formed the interior shape of die cavity and the profile of rocket projectile jet pipe is complementary, and the volution inwall is processed with the internal thread that the external screw thread with rocket projectile jet pipe back segment is complementary; The volution upper end is processed with the rotation screw; The stopping ring is placed on volution upper end, and the stopping ring fixes through hold-down bolt and lower bolster, compresses volution and internal mold, and prevention volution and internal mold move up in pressing process, and stopping ring center is processed with the patrix pilot hole; The cope match-plate pattern lower end is patrix fixedly, and the cope match-plate pattern upper end is connected with press device, and patrix leading portion profile is consistent with the interior shape of rocket projectile jet pipe back segment, and the patrix pilot hole internal diameter of patrix back segment external diameter and stopping ring is complementary.
The course of work:
During compacting, the mould material of in die cavity, packing into to the pressurization of the mould material in the die cavity, after compacting is accomplished, unclamps the fixing hold-down bolt of stopping ring and lower bolster through press device control patrix, removes the stopping ring; In the stepped through hole of lower bolster 1, upwards promote counterdie, make counterdie, the compacting after product, internal mold and volution break away from external mold simultaneously; Rotation screw through on the volution unloads volution, unties the snap ring of forming internal mold awl tube, and internal mold and product are broken away from; Knock counterdie from rocket projectile jet pipe inside at last, counterdie is broken away from, accomplish mould unloading.
Beneficial effect:
The whole compression molding forming mould structure of the utility model is simple, is convenient in demoulding, and has realized the integral body compacting to the rocket projectile jet pipe, has reduced manufacturing procedure and process-cycle, has improved production efficiency, good product consistency.
Description of drawings
Fig. 1 is the overall structure sketch map of rocket projectile jet pipe;
Fig. 2 is the structural profile sketch map of the utility model compression molding forming mould;
Wherein, 1-lower bolster; The 2-screw; The 3-external mold; The 4-counterdie; 5-rocket projectile jet pipe metal shell; The 6-internal mold; The 7-snap ring, the 8-volution; 9-stopping ring; The 10-hold-down bolt; The 11-patrix; The 12-cope match-plate pattern.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the content of the utility model is further specified.
Embodiment
The whole compression molding forming mould of a kind of rocket projectile jet pipe of the utility model, as shown in Figure 2, comprise lower bolster 1, external mold 3, counterdie 4, internal mold 6, volution 8, stopping ring 9, hold-down bolt 10, patrix 11, cope match-plate pattern 12;
During compacting, the mould material of in die cavity, packing into is controlled patrix to the pressurization of the mould material in the die cavity through press device, after compacting is accomplished, unclamps the hold-down bolt 10 that stopping ring 9 and lower bolster 1 are fixed, and removes stopping ring 9; In the stepped through hole of lower bolster 1, upwards promote counterdie 4, make counterdie 4, the compacting after product, internal mold 6 and volution 8 break away from external mold simultaneously; Rotation screw through on the volution 8 unloads volution 8, unties the snap ring 7 of forming internal mold 6 awl tubes, and internal mold and product are broken away from; Knock counterdie 4 from rocket projectile jet pipe inside at last, counterdie 4 is broken away from, accomplish mould unloading.
Claims (1)
1. the whole compression molding forming mould of rocket projectile jet pipe is characterized in that comprising: lower bolster (1), external mold (3), counterdie (4), internal mold (6), volution (8), stopping ring (9), hold-down bolt (10), patrix (11), cope match-plate pattern (12);
Lower bolster (1) upper surface is processed with stepped through hole, and counterdie (4) lower end is through stepped through hole and lower bolster (1) screens, and the profile of counterdie (4) upper end is consistent with the interior shape of rocket projectile jet pipe leading portion, and internal mold (6) is for forming two bulk-breakings of awl barrel structure; External mold (3) is enclosed within outside the counterdie (4) and lower bolster (1) screw is fixed; External mold (3) inner chamber is put into internal mold (6) and the volution (8) behind rocket projectile jet pipe metal shell (5), the composition awl tube successively; Internal mold (6) and volution (8) are formed the interior shape of die cavity and the profile of rocket projectile jet pipe is complementary, and volution (8) inwall is processed with the internal thread that the external screw thread with rocket projectile jet pipe back segment is complementary; Volution (8) upper end is processed with the rotation screw; Stopping ring (9) is placed on volution (8) upper end; And stopping ring (9) is fixing through hold-down bolt (10) and lower bolster (1); Compress volution (8) and internal mold (6), stop volution (8) and internal mold (6) in pressing process, to move up, stopping ring (9) center is processed with the patrix pilot hole; Cope match-plate pattern (12) lower end is patrix (11) fixedly, and cope match-plate pattern (12) upper end is connected with press device, and patrix (11) leading portion profile is consistent with the interior shape of rocket projectile jet pipe back segment, and the patrix pilot hole internal diameter of patrix (11) back segment external diameter and stopping ring (9) is complementary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120361765XU CN202225363U (en) | 2011-09-26 | 2011-09-26 | Integral compression molding mould for rocket shell ejecting pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120361765XU CN202225363U (en) | 2011-09-26 | 2011-09-26 | Integral compression molding mould for rocket shell ejecting pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202225363U true CN202225363U (en) | 2012-05-23 |
Family
ID=46075967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120361765XU Expired - Fee Related CN202225363U (en) | 2011-09-26 | 2011-09-26 | Integral compression molding mould for rocket shell ejecting pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202225363U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717461A (en) * | 2012-06-27 | 2012-10-10 | 晋西工业集团有限责任公司 | Overall compression molding mold for rocket ammunition jet pipe with support lugs |
| JP2021028176A (en) * | 2020-11-26 | 2021-02-25 | 株式会社栗本鐵工所 | Method for manufacturing hollow cylindrical body |
| CN116872530A (en) * | 2023-07-26 | 2023-10-13 | 天津爱思达航天科技股份有限公司 | A mold for aircraft head shell and its molding method |
-
2011
- 2011-09-26 CN CN201120361765XU patent/CN202225363U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717461A (en) * | 2012-06-27 | 2012-10-10 | 晋西工业集团有限责任公司 | Overall compression molding mold for rocket ammunition jet pipe with support lugs |
| JP2021028176A (en) * | 2020-11-26 | 2021-02-25 | 株式会社栗本鐵工所 | Method for manufacturing hollow cylindrical body |
| CN116872530A (en) * | 2023-07-26 | 2023-10-13 | 天津爱思达航天科技股份有限公司 | A mold for aircraft head shell and its molding method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120523 Termination date: 20140926 |
|
| EXPY | Termination of patent right or utility model |