CN210996381U - Die-casting mold core capable of realizing one-step molding of aircraft tail wing - Google Patents
Die-casting mold core capable of realizing one-step molding of aircraft tail wing Download PDFInfo
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- CN210996381U CN210996381U CN201921796304.8U CN201921796304U CN210996381U CN 210996381 U CN210996381 U CN 210996381U CN 201921796304 U CN201921796304 U CN 201921796304U CN 210996381 U CN210996381 U CN 210996381U
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Abstract
The utility model discloses a die casting mold core capable of realizing one-step molding of an aircraft empennage, 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 utility model provides a current degree of difficulty that adopts other modes to carry out processing to the aircraft fin big, with high costs, the harsh problem of processing conditions.
Description
Technical Field
The utility model relates to a die-casting device designs technical field, concretely relates to can realize aircraft fin one shot forming's die-casting mold core.
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 utility model discloses the technical problem that will solve is: the die-casting die core capable of realizing one-step forming of the tail wing of the aircraft is provided to solve the problems that the difficulty of machining the tail wing of the structure in other modes is high, the cost is high and the machining conditions are harsh at present.
In order to solve the above problem, the utility model provides a 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 utility model discloses beneficial effect:
the utility model discloses fin to opening on there is the type hole has designed a new die-casting mold core, through set up special-shaped platform chamber on being provided with the front and back mold core that corresponds fin structure die cavity, and set up the shaping hole at special-shaped platform chamber middle part, and as the mold core structure of shaping hole through the polished rod, and then satisfied the processing to the type hole effectively, realized to the holistic direct die-casting shaping of fin, reduced subsequent machining allowance, and then make continuous rapid processing go-between become reality, improved efficiency and reduced the cost of processing, on the other hand, the utility model discloses the structure still has simply, advantages such as simple operation.
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.
In the embodiment, the slag discharging cavities 1A are all L-type or Z-type structures, and meanwhile, one end of each slag discharging cavity 1A, which is connected with the side edge of the front mold core 1, is parallel to one end of the front mold core 1.
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.
When the utility model discloses the device carries out fin die-casting shaping in using this embodiment, can refer to following step and go on:
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 (8)
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 (2); 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921796304.8U CN210996381U (en) | 2019-10-24 | 2019-10-24 | Die-casting mold core capable of realizing one-step molding of aircraft tail wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921796304.8U CN210996381U (en) | 2019-10-24 | 2019-10-24 | Die-casting mold core capable of realizing one-step molding of aircraft tail wing |
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| CN210996381U true CN210996381U (en) | 2020-07-14 |
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| CN201921796304.8U Active CN210996381U (en) | 2019-10-24 | 2019-10-24 | Die-casting mold core capable of realizing one-step molding of aircraft tail wing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756768A (en) * | 2019-10-24 | 2020-02-07 | 贵州裕高电子有限责任公司 | Die-casting mold core capable of realizing one-step molding of aircraft empennage and using method thereof |
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2019
- 2019-10-24 CN CN201921796304.8U patent/CN210996381U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756768A (en) * | 2019-10-24 | 2020-02-07 | 贵州裕高电子有限责任公司 | Die-casting mold core capable of realizing one-step molding of aircraft empennage and using method thereof |
| CN110756768B (en) * | 2019-10-24 | 2023-12-29 | 贵州裕高电子有限责任公司 | Die casting mold core capable of realizing one-step molding of tail wing of aircraft and use method thereof |
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