CN110756768B - Die casting mold core capable of realizing one-step molding of tail wing of aircraft and use method thereof - Google Patents
Die casting mold core capable of realizing one-step molding of tail wing of aircraft and use method thereof Download PDFInfo
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- CN110756768B CN110756768B CN201911016576.6A CN201911016576A CN110756768B CN 110756768 B CN110756768 B CN 110756768B CN 201911016576 A CN201911016576 A CN 201911016576A CN 110756768 B CN110756768 B CN 110756768B
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- mold core
- cavity
- tail wing
- tail
- front mold
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- 238000004512 die casting Methods 0.000 title claims abstract description 28
- 238000000465 moulding Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000007599 discharging Methods 0.000 claims abstract description 29
- 239000002893 slag Substances 0.000 claims abstract description 29
- 239000000463 material Substances 0.000 claims description 7
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 2
- 238000003754 machining Methods 0.000 description 3
- 239000002184 metal Substances 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D17/00—Pressure die casting or injection die casting, i.e. casting in which the metal is forced into a mould under high pressure
- B22D17/20—Accessories: Details
- B22D17/22—Dies; Die plates; Die supports; Cooling equipment for dies; Accessories for loosening and ejecting castings from dies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention discloses a die-casting mold core capable of realizing one-step molding of an aircraft tail wing and a use method thereof, belonging to the technical field of die-casting device design; the mold comprises a front mold core and a rear mold core which are matched with each other; the middle parts of two end surfaces of the front mold core and the rear mold core which are attached are provided with tail wing cavities in a trapezoid structure; the bottom edge of the tail wing cavity is also provided with a special-shaped table cavity; a forming hole is formed in the middle of the special-shaped table cavity; a feeding groove is arranged on the front mold core and the rear mold core and is attached to the bottom edge of the tail cavity; a slag discharging cavity is also arranged on the front mold core at the position close to the upper top edge and the two side edges of the tail wing cavity; a connecting groove is also arranged between the slag discharging cavity and the side edge of the front mold core; a feeding hole is formed in one side, opposite to the bottom edge of the tail wing cavity, of the rear mold core along the thickness direction of the rear mold core; the feeding hole is communicated with the feeding groove; the invention solves the problems of high difficulty, high cost and severe processing conditions of the tail wing of the aircraft by adopting other modes at present.
Description
Technical Field
The invention relates to the technical field of die casting device design, in particular to a die casting mold core capable of realizing one-step molding of an aircraft tail wing and a use method thereof.
Background
The tail fin of an aircraft is the key for determining the performance of the aircraft, most of the tail fin structures of the aircraft are almost the same, and the surface quality, the weight, the size coordination and the service performance after forming are strictly required on devices with higher requirements on aerodynamic performance such as the aircraft, so the existing tail fin structure is mostly processed by adopting a sheet metal machining method, but the existing tail fin structure of the aircraft is provided with two coaxial positioning holes in the thickness direction as a structure mounted on the aircraft, and the existing tail fin structure is generally processed by other machining methods after sheet metal machining is firstly processed on the type hole structure, but the processing process is easy to influence the integral structure of the tail fin because the tail fin belongs to thin-wall parts, and only a high-precision machine tool can be adopted to meet the effective processing requirement, so the device capable of solving the problems of high difficulty, high production cost and harsh processing conditions of the tail fin structure at present is needed.
Disclosure of Invention
The technical problems to be solved by the invention are as follows: the die-casting mold core capable of realizing one-step molding of the tail wing of the aircraft and the use method thereof are provided, so that the problems of high difficulty, high cost and severe processing conditions in the existing processing of the tail wing of the structure by adopting other modes are solved.
In order to solve the problems, the invention provides the following technical scheme:
a die casting mold core capable of realizing one-step molding of an aircraft tail wing comprises a front mold core and a rear mold core which are matched with each other; the middle parts of two end surfaces of the front mold core and the rear mold core which are attached are provided with tail wing cavities in a trapezoid structure; the bottom edge of the tail wing cavity is also provided with a special-shaped table cavity; a forming hole is formed in the middle of the special-shaped table cavity; a feeding groove is arranged on the front mold core and the rear mold core and is attached to the bottom edge of the tail cavity; a slag discharging cavity is also arranged on the front mold core at the position close to the upper top edge and the two side edges of the tail wing cavity; a connecting groove is also arranged between the slag discharging cavity and the side edge of the front mold core; a feeding hole is formed in one side, opposite to the bottom edge of the tail wing cavity, of the rear mold core along the thickness direction of the rear mold core; the feeding hole is communicated with the feeding groove.
Preferably, the slag discharging cavities are 8 in number, 2 are arranged at the upper top edge of the tail fin cavity, and 3 are respectively arranged at the two side edges of the tail fin cavity; each deslagging cavity is correspondingly provided with a connecting groove.
Further, a slag discharging cavity arranged on the upper top edge of the tail cavity and the other ends of connecting grooves corresponding to the three slag discharging cavities adjacent to the slag discharging cavity on the side edge of the tail cavity are arranged at the side end of the front mold core.
Preferably, the outer side of the upper tail wing cavity on the front mold core is provided with a plurality of ejector rod perforations along the thickness direction of the front mold core.
Furthermore, the slag discharging cavities at the two sides of the tail cavity are respectively provided with a push rod perforation.
Preferably, the length of the connecting part of the feeding groove and the tail wing cavity is not lower than the upper top edge of the tail wing cavity and not higher than the length of the lower top edge, and the special-shaped table cavity is positioned above the feeding groove.
Preferably, the two forming holes arranged on the front mold core and the rear mold core are respectively a through hole structure and a blind hole structure.
Further comprises a polish rod; the polish rod is detachably inserted into the forming hole for setting.
The invention also discloses a use method of the die casting mold core capable of realizing one-step molding of the tail wing of the aircraft,
s1, oppositely placing tail wing cavities on a front mold core and a rear mold core, and then closing the front mold core and the rear mold core according to the positions and locking and fixing the front mold core and the rear mold core;
s2, inserting the polished rod into the forming hole on the front mold core, and tightly attaching the insertion end of the polished rod to the bottom of the forming hole of the blind hole structure on the rear mold core;
s3, pouring the material in a molten state into the tail cavity along the feeding groove through the feeding hole on the rear mold core for molding and die casting;
s4, after the material flows out along the connecting groove, die casting of the workpiece is completed;
s5, removing the polish rod, releasing the locking state of the front mold core and the rear mold core, opening the front mold core and the rear mold core which are stuck together, and then using the ejector rod to eject the workpiece out of the tail wing cavity on the front mold core by penetrating the ejector rod through the ejector rod perforation, thus completing the die casting operation.
The invention has the beneficial effects that:
the invention designs a novel die-casting mold core aiming at the empennage with the shaped holes, the front mold core and the rear mold core which are provided with the corresponding cavities of the empennage structure are provided with the special-shaped table cavities, the middle part of each special-shaped table cavity is provided with the shaping holes, and the polished rod is used as the mold core structure of the shaping holes, so that the processing of the shaped holes is effectively satisfied, the integral direct die-casting molding of the empennage is realized, the subsequent processing allowance is reduced, the continuous and rapid processing of the connecting ring is realized, the efficiency is improved, the processing cost is reduced, and on the other hand, the structure of the invention is simple, the operation is convenient and the like.
Drawings
FIG. 1 is a three-dimensional exploded view of a front mold core, a rear mold core and a workpiece in this embodiment;
FIG. 2 is another directional view of FIG. 1;
FIG. 3 is a schematic view of the three-dimensional structure of the front mold core in the present embodiment;
FIG. 4 is a schematic view of the three-dimensional structure of the rear mold core in the present embodiment;
fig. 5 is a schematic view of a three-dimensional structure of a work piece to be machined in the present embodiment.
Reference numerals illustrate: 1. front mold core, 1A, slag discharging cavity, 1B, connecting groove, 1C, ejector rod perforation, 2, rear mold core, 2A, feeding hole, 3, fin cavity, 3A, special-shaped table cavity, 3B, forming hole, 4, feeding groove.
Detailed Description
The invention will be further described with reference to the accompanying drawings and specific examples:
examples:
referring to fig. 1, the present embodiment provides a die casting mold core capable of realizing one-step molding of an aircraft tail wing, which comprises a front mold core 1 and a rear mold core 2 which are matched with each other; tail wing cavities 3 with trapezoid structures are formed in the middle of two end faces, where the front mold core 1 and the rear mold core 2 are attached; the bottom edge of the tail fin cavity 3 is also provided with a special-shaped table cavity 3A; a forming hole 3B is formed in the middle of the special-shaped table cavity 3A; a feeding groove 4 is also arranged on the front mold core 1 and the rear mold core 2 and is attached to the bottom edge of the tail cavity 3; a slag discharging cavity 1A is also arranged on the front mold core 1 near the top edge and two side edges of the tail fin cavity 3; a connecting groove 1B is also arranged between the slag discharging cavity 1A and the side edge of the front mold core 1; a feeding hole 2A is formed in one side, opposite to the bottom edge of the tail wing cavity 3, of the rear mold core 2 along the thickness direction of the rear mold core 2; the feeding hole 2A is communicated with the feeding groove 4.
The slag discharging cavities 1A are 8 in number, 2 are arranged on the upper top edge of the tail fin cavity 3, and 3 are respectively arranged on two side edges of the tail fin cavity 3; each slag discharging cavity 1A is correspondingly provided with a connecting groove 1B. The evenly distributed slag discharging cavities 1A take the structural characteristics of the tail cavity 3 into consideration, and in this embodiment, the sizes of two slag discharging cavities 1A close to the upper top edge of the tail cavity 3 are larger than the sizes of four slag discharging cavities 1A below, and since the feeding material will cover from bottom to top along the tail cavity 3, the gas in the tail cavity 3 will be concentrated at the upper top edge, so that the slag discharging cavities 1A on two sides of the tail cavity are made larger, so as to control the consistency of the pressure sizes of the cavities.
The other ends of the connecting grooves 1B corresponding to the three slag discharging cavities 1A adjacent to the slag discharging cavity 1A at the side edge of the tail fin cavity 3 are arranged at the side end of the front mold core 1. In this embodiment, the deslagging cavities 1A are all L-shaped or Z-shaped structures, and meanwhile, one end of each deslagging cavity 1A connected with the side edge of the front mold core 1 is parallel.
The outer side of the tail fin cavity 3 on the front mold core 1 is provided with a plurality of ejector rod perforations 1C along the thickness direction of the front mold core 1. And the slag discharging cavities 1A at the two sides of the tail fin cavity 3 are respectively provided with a push rod perforation 1C. The purpose of arranging the ejector rod perforation 1C on the slag discharging cavity 1A is mainly to ensure that the workpiece can be penetrated out along the ejector rod perforation 1C through the ejector rod after die sinking, and the surface of the workpiece can not be damaged when the workpiece is taken down from the front die core 1.
The length of the connecting part of the feeding groove 4 and the tail cavity 3 is not lower than the upper top edge of the tail cavity 3 and not higher than the length of the lower top edge, and the special-shaped table cavity 3A is positioned above the feeding groove 4. In this embodiment, the feeding groove 4 is of a T-shaped structure with an upper size and a lower size, and this structure is mainly used for increasing the contact surface size between the feeding groove and the tail cavity 3.
The two forming holes 3B arranged on the front mold core 1 and the rear mold core 2 are respectively a through hole structure and a blind hole structure. The polishing device also comprises a polished rod; the polish rod is detachably inserted into the molding hole 3B to be set.
The invention also discloses a use method of the die casting mold core capable of realizing one-step molding of the tail wing of the aircraft,
s1, oppositely placing tail wing cavities 3 on a front mold core 1 and a rear mold core 2, and then closing the front mold core 1 and the rear mold core 2 according to the positions and locking and fixing the front mold core 1 and the rear mold core 2; in the embodiment, the front mold core 1 and the rear mold core 2 are folded and then placed in a shell with an internal structure matched with the external dimensions of the front mold core and the rear mold core for locking and fixing;
s2, inserting a polished rod along a forming hole 3B on the front mold core 1, and tightly attaching the insertion end of the polished rod to the bottom of the forming hole 3B with a blind hole structure on the rear mold core 2;
s3, pouring the material in a molten state into the tail cavity 3 along a feeding groove through a feeding hole 2A on the rear mold core 2 for molding and die casting;
s4, after the material flows out along the connecting groove 1B, die casting of the workpiece is completed;
s5, removing the polish rod, releasing the locking state of the front mold core 1 and the rear mold core 2, opening the mold of the front mold core 1 and the rear mold core 2 which are stuck together, and then using the ejector rod to eject the workpiece out of the tail wing cavity 3 on the front mold core 1 through the ejector rod perforation 1C, thus completing the die casting operation.
Claims (6)
1. The die-casting mold core capable of realizing one-step molding of the tail wing of the aircraft comprises a front mold core (1) and a rear mold core (2) which are matched with each other; the method is characterized in that: tail wing cavities (3) with trapezoid structures are formed in the middle positions of two end faces, where the front mold core (1) and the rear mold core (2) are attached; the bottom edge of the tail wing cavity (3) is also provided with a special-shaped table cavity (3A); a forming hole (3B) is formed in the middle of the special-shaped table cavity (3A); a feeding groove (4) is arranged at the position of the front mold core (1) and the rear mold core (2) which is attached to the bottom edge of the tail wing cavity (3); a slag discharging cavity (1A) is also arranged on the front mold core (1) at the positions close to the top edge and the two side edges of the tail wing cavity (3); a connecting groove (1B) is also arranged between the slag discharging cavity (1A) and the side edge of the front mold core (1); a feeding hole (2A) is formed in one side, opposite to the bottom edge of the tail wing cavity (3), of the rear mold core (2) along the thickness direction of the rear mold core (2); the feeding hole (2A) is communicated with the feeding groove (4), one slag discharging cavity (1A) is arranged on the upper top edge of the tail fin cavity (3), and the other ends of connecting grooves (1B) corresponding to three slag discharging cavities (1A) adjacent to the slag discharging cavity (1A) at the side edge of the tail fin cavity (3) are arranged at the side end of the front mold core (1); the outer side of the tail wing cavity (3) on the front mold core (1) is provided with a plurality of ejector rod perforations (1C) along the thickness direction of the front mold core (1); and ejector rod perforations (1C) are arranged on slag discharging cavities (1A) on two sides of the tail wing cavity (3).
2. A die casting mold core capable of realizing one-step molding of an aircraft tail wing according to claim 1, wherein: the slag discharging cavities (1A) are 8 in number, 2 are arranged at the upper top edge of the tail fin cavity (3), and 3 are respectively arranged at the two side edges of the tail fin cavity (3); each deslagging cavity (1A) is correspondingly provided with a connecting groove (1B).
3. A die casting mold core capable of realizing one-step molding of an aircraft tail wing according to claim 1, wherein: the length of the connecting part of the feeding groove (4) and the tail wing cavity (3) is not lower than the upper top edge of the tail wing cavity (3), and is not higher than the length of the lower top edge, and the special-shaped table cavity (3A) is positioned above the feeding groove (4).
4. A die casting mold core capable of realizing one-step molding of an aircraft tail wing according to claim 1, wherein: two forming holes (3B) arranged on the front mold core (1) and the rear mold core (2) are respectively in a through hole structure and a blind hole structure.
5. A die casting core for realizing one-time molding of an aircraft tail according to claim 1 or 4, wherein: the polishing device also comprises a polished rod; the polish rod is detachably inserted into the forming hole (3B) for setting.
6. The method for using the die casting mold core capable of realizing one-step molding of the tail wing of the aircraft according to claim 5, wherein the method comprises the following steps of:
s1, oppositely placing tail wing cavities (3) on a front mold core (1) and a rear mold core (2), and locking and fixing the front mold core (1) and the rear mold core (2) after folding according to the positions;
s2, inserting the polished rod into the forming hole (3B) on the front mold core (1), and tightly attaching the insertion end of the polished rod to the bottom of the forming hole (3B) with the blind hole structure on the rear mold core (2);
s3, forming and die-casting the material in a molten state along a feeding groove (4) and tail wing cavity (3) through a feeding hole (2A) on the rear mold core (2);
s4, after the material flows out along the connecting groove (1B), die casting of the workpiece is completed;
s5, unloading the polished rod, releasing the locking state of the front mold core (1) and the rear mold core (2), opening the mold of the front mold core (1) and the rear mold core (2) which are stuck together, and then using the ejector rod to penetrate through the ejector rod perforation (1C) to eject the workpiece from the tail wing cavity (3) on the front mold core (1) so as to finish the die casting operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911016576.6A CN110756768B (en) | 2019-10-24 | 2019-10-24 | Die casting mold core capable of realizing one-step molding of tail wing of aircraft and use method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911016576.6A CN110756768B (en) | 2019-10-24 | 2019-10-24 | Die casting mold core capable of realizing one-step molding of tail wing of aircraft and use method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110756768A CN110756768A (en) | 2020-02-07 |
| CN110756768B true CN110756768B (en) | 2023-12-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911016576.6A Active CN110756768B (en) | 2019-10-24 | 2019-10-24 | Die casting mold core capable of realizing one-step molding of tail wing of aircraft and use method thereof |
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| CN (1) | CN110756768B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112338163B (en) * | 2020-10-21 | 2022-04-01 | 重庆博奥镁铝金属制造有限公司 | Die-casting processing method for product with isolated structure |
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| JP2001212659A (en) * | 2000-12-27 | 2001-08-07 | Atsuta Kigyo Kk | Winglike member die casting method |
| CN102581254A (en) * | 2012-03-08 | 2012-07-18 | 宁波华朔模具机械有限公司 | Die structure with assembly for obliquely pulling core in sliding blocks |
| CN204018679U (en) * | 2014-07-14 | 2014-12-17 | 东莞市石碣宏钰模具五金厂 | A kind of stern rudder die casting |
| CN106735061A (en) * | 2016-12-22 | 2017-05-31 | 宁波杰达模具机械有限公司 | A kind of die casting for facilitating housing to be molded |
| CN210996381U (en) * | 2019-10-24 | 2020-07-14 | 贵州裕高电子有限责任公司 | Die-casting mold core capable of realizing one-step molding of aircraft tail wing |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010002617A1 (en) * | 1998-12-23 | 2001-06-07 | United Technologies Corporation | Apparatus and methods for die casting |
| US20130025816A1 (en) * | 2011-07-29 | 2013-01-31 | Bochiechio Mario P | Die casting system and method |
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2019
- 2019-10-24 CN CN201911016576.6A patent/CN110756768B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001212659A (en) * | 2000-12-27 | 2001-08-07 | Atsuta Kigyo Kk | Winglike member die casting method |
| CN102581254A (en) * | 2012-03-08 | 2012-07-18 | 宁波华朔模具机械有限公司 | Die structure with assembly for obliquely pulling core in sliding blocks |
| CN204018679U (en) * | 2014-07-14 | 2014-12-17 | 东莞市石碣宏钰模具五金厂 | A kind of stern rudder die casting |
| CN106735061A (en) * | 2016-12-22 | 2017-05-31 | 宁波杰达模具机械有限公司 | A kind of die casting for facilitating housing to be molded |
| CN210996381U (en) * | 2019-10-24 | 2020-07-14 | 贵州裕高电子有限责任公司 | Die-casting mold core capable of realizing one-step molding of aircraft tail wing |
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| CN110756768A (en) | 2020-02-07 |
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