CN110756768A - Die-casting mold core capable of realizing one-step molding of aircraft empennage and using method thereof - Google Patents
Die-casting mold core capable of realizing one-step molding of aircraft empennage and using method thereof Download PDFInfo
- Publication number
- CN110756768A CN110756768A CN201911016576.6A CN201911016576A CN110756768A CN 110756768 A CN110756768 A CN 110756768A CN 201911016576 A CN201911016576 A CN 201911016576A CN 110756768 A CN110756768 A CN 110756768A
- Authority
- CN
- China
- Prior art keywords
- mold core
- cavity
- empennage
- die
- front mold
- 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.)
- Granted
Links
- 238000004512 die casting Methods 0.000 title claims abstract description 32
- 238000000465 moulding Methods 0.000 title claims abstract description 15
- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000002893 slag Substances 0.000 claims abstract description 39
- 238000007599 discharging Methods 0.000 claims abstract description 35
- 239000000463 material Substances 0.000 claims description 5
- 239000012768 molten material Substances 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 2
- 239000002184 metal Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention discloses a die-casting die core capable of realizing one-step molding of an aircraft empennage and a using 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 where the front mold core and the rear mold core are attached are provided with tail wing cavities in a trapezoidal structure; the bottom edge of the empennage cavity is also provided with a special-shaped platform cavity; a forming hole is formed in the middle of the special-shaped table cavity; feeding grooves are also arranged at the positions, which are attached to the bottom edge of the empennage cavity, of the front mold core and the rear mold core; slag discharging cavities are formed in the positions, close to the upper top edge and the two side edges of the empennage cavity, of the front mold core; a connecting groove is 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 empennage 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 harsh processing conditions of processing the empennage of the aircraft by other methods at present.
Description
Technical Field
The invention relates to the technical field of die-casting device design, in particular to a die-casting die core capable of realizing one-step molding of an aircraft empennage and a using method thereof.
Background
The empennages of aircrafts are the key for determining the performance of the aircrafts, most of the empennages of the aircrafts are almost the same in structure, the surface quality, the weight, the size compatibility and the use performance after forming of the empennages of the aircrafts have strict requirements, so most of the prior empennages are processed by means of sheet metal processing, but the empennages of the aircrafts like the empennages in figure 5 are provided with two coaxial positioning holes in the thickness direction respectively to be used as structures installed on the aircrafts, generally speaking, most of the empennages of the structure are processed by sheet metal processing and other machining modes, but the empennages are thin-walled parts, the processing process is easy to influence the whole structure, effective processing needs can be met only by adopting a high-precision machine tool, so that the difficulty in processing the empennages of the structure is high at the present stage, the device with the problems of high production cost and harsh processing conditions is needed at present.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the die-casting die core capable of realizing one-step forming of the empennage of the aircraft and the using method thereof are provided, so that the problems of high difficulty, high cost and harsh processing conditions of processing the empennage of the structure in other modes at present 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 empennage comprises a front mold core and a rear mold core which are matched with each other; the middle parts of two end surfaces where the front mold core and the rear mold core are attached are provided with tail wing cavities in a trapezoidal structure; the bottom edge of the empennage cavity is also provided with a special-shaped platform cavity; a forming hole is formed in the middle of the special-shaped table cavity; feeding grooves are also arranged at the positions, which are attached to the bottom edge of the empennage cavity, of the front mold core and the rear mold core; slag discharging cavities are formed in the positions, close to the upper top edge and the two side edges of the empennage cavity, of the front mold core; a connecting groove is 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 empennage 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 number of the slag discharging cavities is 8, the number of the slag discharging cavities is 2 on the upper top edge of the empennage cavity, and the number of the slag discharging cavities is 3 on two side edges of the empennage cavity; each slag discharging cavity is correspondingly provided with a connecting groove.
Furthermore, a slag discharging cavity is arranged on the upper top edge of the empennage cavity, and the other ends of connecting grooves corresponding to three slag discharging cavities adjacent to the slag discharging cavity on the side edge of the empennage 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 also provided with a plurality of ejector rod through holes along the thickness direction of the front mold core.
Furthermore, ejector rod through holes are arranged on the slag discharging cavities on the two side edges of the empennage cavity.
Preferably, the length of the feeding groove connected with the empennage cavity is not less than the length of the upper top edge of the empennage cavity and not more than the length of the lower top edge, and the special-shaped platform cavity is located above the feeding groove.
Preferably, the two forming holes arranged on the front mold core and the rear mold core are respectively of a through hole structure and a blind hole structure.
The device further comprises a polish rod; the polished rod is detachably inserted into the forming hole for setting.
The invention also discloses a use method of the die-casting die core capable of realizing one-step molding of the tail wing of the aircraft,
s1, oppositely placing empennage cavities on the front mold core and the rear mold core, folding 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 polish rod into the forming hole on the front mold core, and tightly attaching the inserted end of the polish rod to the bottom of the forming hole of the blind hole structure on the rear mold core;
s3, pouring the molten material into the empennage cavity along the feeding groove through the feeding hole on the rear die core for molding and die casting;
s4, completing die casting of the workpiece after the material flows out along the connecting groove;
and S5, unloading 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 attached together, and ejecting the workpiece from the empennage cavity on the front mold core by penetrating the ejector rod through hole by using the ejector rod, thereby completing the die casting operation.
The invention has the beneficial effects that:
the invention designs a novel die-casting die core aiming at the empennage with the profile holes, the front die core and the rear die core which are provided with cavities corresponding to empennage structures are provided with special-shaped platform cavities, the middle parts of the special-shaped platform cavities are provided with forming holes, and the polished rods are used as the die core structures of the forming holes, so that the processing of the profile holes is effectively met, the integral direct die-casting forming of the empennage is realized, the subsequent processing allowance is reduced, the continuous and rapid processing of the connecting rings is realized, the efficiency is improved, the processing cost is reduced, and on the other hand, the structure of the die-casting die core has the advantages of simplicity, convenience in operation and the like.
Drawings
FIG. 1 is a three-dimensional exploded view of the front mold core, the rear mold core and the workpiece in this embodiment;
FIG. 2 is another directional view of FIG. 1;
FIG. 3 is a schematic three-dimensional structure of the front core in the present embodiment;
FIG. 4 is a schematic three-dimensional structure of the rear core in the present embodiment;
fig. 5 is a schematic three-dimensional structure diagram of the workpiece to be machined in the present embodiment.
Description of reference numerals: 1. the mold comprises a front mold core, a slag discharging cavity 1A, a connecting groove 1B, a mandril through hole 1C, a rear mold core 2, a feeding hole 2A, a tail wing cavity 3, a special-shaped platform cavity 3A, a forming hole 3B, a forming hole 4 and a feeding groove.
Detailed Description
The invention will be further described with reference to the following drawings and specific embodiments:
example (b):
referring to fig. 1, the embodiment provides a die-casting mold core capable of realizing one-step molding of an aircraft empennage, which comprises a front mold core 1 and a rear mold core 2 which are matched with each other; the middle parts of two end surfaces where the front mold core 1 and the rear mold core 2 are attached are provided with tail wing cavities 3 in a trapezoidal structure; the bottom edge of the empennage cavity 3 is also provided with a special-shaped platform 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 at the position where the front mold core 1 and the rear mold core 2 are attached to the bottom edge of the empennage cavity 3; a slag discharging cavity 1A is also formed in the position, close to the upper top edge and the two side edges of the empennage cavity 3, of the front mold core 1; a connecting groove 1B is 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 of the rear mold core 2, which is opposite to the bottom edge of the empennage cavity 3, along the thickness direction of the rear mold core 1; the feeding hole 2A is communicated with the feeding groove 4.
The number of the slag discharge cavities 1A is 8, the number of the slag discharge cavities is 2 on the upper top edge of the tail wing cavity 3, and the number of the slag discharge cavities is 3 on the two side edges of the tail wing cavity 3; each slag discharging cavity 1A is correspondingly provided with a connecting groove 1B. The slag discharging cavities 1A which are uniformly distributed take the structural characteristics of the tail wing cavity 3 into consideration, and two slag discharging cavities 1A which are close to the upper top edge of the tail wing cavity 3 are larger than four slag discharging cavities 1A below the tail wing cavity in the embodiment.
A slag discharging cavity 1A arranged on the upper top edge of the empennage cavity 3, and the other ends of connecting grooves 1B corresponding to the three slag discharging cavities 1A adjacent to the slag discharging cavity 1A on the side edge of the empennage cavity 3 are arranged at the side end of the front mold core 1. In this embodiment, the slag discharging cavities 1A are all L-shaped or Z-shaped, and the ends of the slag discharging cavities 1A connected to the side of the front mold core 1 are all parallel.
A plurality of ejector rod through holes 1C are arranged on the outer side of the empennage cavity 3 on the front mold core 1 along the thickness direction of the front mold core 1. And ejector rod through holes 1C are arranged on the slag discharging cavities 1A on the two side edges of the empennage cavity 3. The purpose of arranging the ejector rod through hole 1C on the slag discharge cavity 1A is mainly to ensure that the ejector rod can penetrate out along the ejector rod through hole 1C after the mold is opened, and the surface of a workpiece cannot be damaged when the workpiece is taken down from the front mold core 1.
The length of the material feeding groove 4 connected with the empennage cavity 3 is not less than the length of the upper top edge of the empennage cavity 3 and not more than the length of the lower top edge, and the special-shaped platform cavity 3A is positioned above the material feeding groove 4. In this embodiment, the feeding grooves 4 are all of a T-shaped structure with a large upper part and a small lower part, and the structure is mainly used for increasing the size of the contact surface between the feeding grooves 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 of a through hole structure and a blind hole structure. The polishing device also comprises a polish 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 die core capable of realizing one-step molding of the tail wing of the aircraft,
s1, oppositely placing the empennage cavities 3 on the front mold core 1 and the rear mold core 2, folding 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 the polish rod along the forming hole 3B on the front mold core 1, and tightly attaching the inserted end to the bottom of the forming hole 3A of the blind hole structure on the rear mold core 2;
s3, pouring the molten material into the empennage cavity 3 along the feeding groove through the feeding hole 2A on the rear die core 2 for molding and die casting;
s4, completing die casting of the workpiece after the material flows out along the connecting groove 1B;
and S5, unloading the polish rod, releasing the locking state of the front mold core 1 and the rear mold core 2, opening the front mold core 1 and the rear mold core 2 which are attached together, and ejecting the workpiece from the empennage cavity 3 on the front mold core 1 by penetrating the ejector rod through hole 1C by using the ejector rod, thus finishing the die casting operation.
Claims (9)
1. A die-casting mold core capable of realizing one-step molding of an aircraft empennage comprises a front mold core (1) and a rear mold core (2) which are matched with each other; the method is characterized in that: the middle parts of two end surfaces of the front mold core (1) and the rear mold core (2) which are attached to each other are provided with tail wing cavities (3) in a trapezoidal structure; the bottom edge of the empennage cavity (3) is also provided with a special-shaped platform 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 at the position where the front mold core (1) and the rear mold core (2) are attached to the bottom edge of the empennage cavity (3); a slag discharging cavity (1A) is also formed in the position, close to the upper top edge and the two side edges of the empennage cavity (3), of the front mold core (1); a connecting groove (1B) is 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 empennage cavity (3), of the rear mold core (2) along the thickness direction of the rear mold core (1); the feeding hole (2A) is communicated with the feeding groove (4).
2. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 1, wherein: the number of the slag discharging cavities (1A) is 8, the number of the slag discharging cavities is 2 on the upper top edge of the empennage cavity (3), and the number of the slag discharging cavities is 3 on the two side edges of the empennage cavity (3); each slag discharging cavity (1A) is correspondingly provided with a connecting groove (1B).
3. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 1 or 2, wherein: the slag discharging cavity (1A) is arranged on the upper top edge of the tail wing cavity (3), and the other ends of connecting grooves (1B) corresponding to three slag discharging cavities (1A) adjacent to the slag discharging cavity (1A) on the side edge of the tail wing cavity (3) are arranged at the side end of the front mold core (1).
4. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 1, wherein: the outer side of the upper empennage cavity (3) on the front mold core (1) is also provided with a plurality of ejector rod through holes (1C) along the thickness direction of the front mold core (1).
5. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 4, wherein: ejector pin through holes (1C) are arranged on the slag discharging cavities (1A) on the two side edges of the empennage cavity (3).
6. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 1, wherein: the length of the feeding groove (4) connected with the empennage cavity (3) is not less than the length of the upper top edge of the empennage cavity (3) and not more than the length of the lower top edge, and the special-shaped platform cavity (3A) is positioned above the feeding groove (4).
7. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 1, wherein: two molding holes (3B) arranged on the front mold core (1) and the rear mold core (2) are respectively of a through hole structure and a blind hole structure.
8. The die-casting die core capable of realizing one-step forming of the tail wing of the aircraft as claimed in claim 1 or 7, wherein: the polishing device also comprises a polish rod; the polish rod is detachably inserted into the forming hole (3B) for setting.
9. The use method of the die-casting die core capable of realizing one-step molding of the tail wing of the aircraft as claimed in any one of claims 1 to 8, is characterized in that:
s1, oppositely placing the empennage cavity (3) on the front mold core (1) and the rear mold core (2), folding 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);
s2, inserting the polish rod along the forming hole (3B) on the front mold core (1), and tightly attaching the inserted end to the bottom of the forming hole (3A) of the blind hole structure on the rear mold core (2);
s3, pouring the molten material into the empennage cavity (3) along the feeding groove through the feeding hole (2A) on the rear die core (2) for molding and die casting;
s4, completing die casting of the workpiece after the material flows out along the connecting groove (1B);
s5, unloading the polish rod, releasing the locking state of the front mold core (1) and the rear mold core (2), opening the front mold core (1) and the rear mold core (2) which are attached together, and ejecting the workpiece from the empennage cavity (3) on the front mold core (1) through the ejector rod through hole (1C) by using an ejector rod to complete 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 true CN110756768A (en) | 2020-02-07 |
| CN110756768B CN110756768B (en) | 2023-12-29 |
Family
ID=69333536
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110756768B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112338163A (en) * | 2020-10-21 | 2021-02-09 | 重庆博奥镁铝金属制造有限公司 | Die-casting processing method for product with isolated structure |
Citations (7)
| 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 |
| 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 |
| US20130025816A1 (en) * | 2011-07-29 | 2013-01-31 | Bochiechio Mario P | Die casting system and method |
| 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 |
-
2019
- 2019-10-24 CN CN201911016576.6A patent/CN110756768B/en active Active
Patent Citations (7)
| 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 |
| JP2001212659A (en) * | 2000-12-27 | 2001-08-07 | Atsuta Kigyo Kk | Winglike member die casting method |
| US20130025816A1 (en) * | 2011-07-29 | 2013-01-31 | Bochiechio Mario P | Die casting system and 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112338163A (en) * | 2020-10-21 | 2021-02-09 | 重庆博奥镁铝金属制造有限公司 | Die-casting processing method for product with isolated structure |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110756768B (en) | 2023-12-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210996381U (en) | Die-casting mold core capable of realizing one-step molding of aircraft tail wing | |
| CN110756768A (en) | Die-casting mold core capable of realizing one-step molding of aircraft empennage and using method thereof | |
| CN201677009U (en) | Middle-layer sand mould with a double-surface inner positioning taper hole | |
| CN209830241U (en) | Foundry goods ejecting device in mould | |
| CN207564878U (en) | A kind of mould slide block twice core pulling structure | |
| CN211101508U (en) | Die casting die for machining empennage of small aircraft | |
| CN112517878A (en) | Die casting die with insert | |
| CN211161843U (en) | Die-casting die of connecting ring capable of being separated from flying device and loaded by airplane | |
| CN214872298U (en) | Thrust rod rubber ball hinge forming die | |
| CN210336363U (en) | Easy-to-detach structure of building component groove-shaped space forming die | |
| CN211218555U (en) | High-efficient golden die casting mould | |
| CN214023405U (en) | Die casting die with insert | |
| CN211135472U (en) | Die-casting die for rear top cover of airplane-mounted detachable flight device | |
| CN112958754A (en) | Local loading forced feeding and core-pulling device of large aluminum alloy extrusion casting die | |
| CN105946144A (en) | Mold core combination structure and machining process thereof | |
| CN210634074U (en) | Intercom is with interior knot position mould of drawing to one side | |
| KR20100089171A (en) | Wax model metalic pattern assembly | |
| CN209811165U (en) | Conjoined casting unit | |
| CN212884946U (en) | Die casting die of controller box | |
| CN214773714U (en) | Ejection mold | |
| CN214000637U (en) | Composite material oil supply tank angle section forming device with L-shaped surface and negative angle | |
| CN211101454U (en) | Sand-casting mould of rear cabin body capable of being detached from flight device and loaded on airplane | |
| CN205112246U (en) | Thin -walled special -shaped piece's injection moulding mould | |
| CN110756769B (en) | Die casting die for processing tail fin of small aircraft and using method thereof | |
| CN214321657U (en) | Split type combined forming female die |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |