CN211101508U - Die casting die for machining empennage of small aircraft - Google Patents
Die casting die for machining empennage of small aircraft Download PDFInfo
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- CN211101508U CN211101508U CN201921796780.XU CN201921796780U CN211101508U CN 211101508 U CN211101508 U CN 211101508U CN 201921796780 U CN201921796780 U CN 201921796780U CN 211101508 U CN211101508 U CN 211101508U
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Abstract
The utility model discloses a die casting die for processing empennage of a small aircraft, which belongs to the technical field of die casting device design, and adopts a front template and a rear template, and is respectively provided with a feeding through hole and a feeding blind hole, and a front mold core and a rear mold core are installed through a mold core installation cavity; a tail fin bottom plate cavity is arranged on the front mold core; a blade cavity is arranged on the rear mold core; the installation of the first empennage connecting pipe core and the second empennage connecting pipe core is completed through the first positioning through hole and the second positioning through hole on the front mold core and the rear mold core, so that the arrangement of an empennage connecting pipe cavity is realized; further setting up feeding subassembly and the pipeline structure that corresponds, set up again and arrange the sediment chamber and arrange sediment, accomplish taking off to the formed part through setting up the ejector pin perforation and ejector pin at last, the utility model provides a current degree of difficulty that adopts other modes to process the aircraft fin is big, and is 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 die casting die of processing small aircraft fin.
Background
The tail fin of the aircraft is a key for determining the performance of the aircraft, and for the tail fin of the aircraft, referring to fig. 1, the tail fin is composed of a bottom plate with a through hole in the middle, a connecting pipe is arranged on the outer diameter of the through hole on one side of the bottom plate, and blades in a radial structure are symmetrically arranged on the periphery of the connecting pipe, normally, for the tail fin, the bottom plate, the connecting pipe and the blades are respectively processed and then fixed by welding, but because an air port is arranged at the position, close to the connecting pipe, of the bottom of any two adjacent blades, the air port is difficult to directly complete through material increase processing, on the other hand, because the structure of the tail fin is complex, if material reduction processing is used, a high-precision machine tool is needed to execute, the mode has high cost and low processing efficiency, the processing difficulty of the tail fin can be effectively reduced at present, and the processing, devices to increase processing rates are in urgent need.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that will solve is: the die-casting die for machining the empennage of the small aircraft and the using method thereof are provided to solve the problems that the machining difficulty of the empennage of the small aircraft is high, the cost is high and the machining conditions are harsh in other methods at present.
In order to solve the above problem, the utility model provides a following technical scheme:
a die casting die for processing a small aircraft empennage comprises a front template and a rear template which are matched with each other; the middle parts of two side end surfaces of the front template and the rear template which are opposite are provided with mold core mounting cavities with square structures; the front template and the rear template are also provided with a feeding through hole and a feeding blind hole which are opposite to each other and are communicated with the die core mounting cavity; a front mold core and a rear mold core which are matched with each other are detachably placed in the mold core mounting cavity; a tail fin bottom plate cavity is formed in the side end face, opposite to the rear mold core, of the front mold core; the slag discharging cavity is arranged at the positions, close to the peripheral sides of the empennage base plate cavity, of the front mold core and the rear mold core, and the front mold core and the rear mold core are both provided with feeding grooves; the feeding groove is respectively communicated with the feeding through hole and the feeding blind hole; a blade cavity in a blind hole structure is further formed in the position, connected with the empennage base plate cavity, of the rear mold core along the thickness direction of the rear mold core, a first positioning through hole is formed in the middle of the empennage base plate cavity, and a second positioning through hole is formed in the position, opposite to the first positioning through hole, of the front mold core; the first tail connecting pipe core and the second tail connecting pipe core respectively penetrate through the first positioning through hole and the second positioning through hole, the first tail connecting pipe core is of a sleeve structure, and the second tail connecting pipe core is of a straight solid pipe structure matched with the sleeve structure; a mandril through hole (9) is arranged at the corresponding position of the rear mold core and the rear mold plate; the ejector rod passes through the ejector rod through hole and is detachably arranged on the rear template; and the feeding assembly is also arranged on the feeding through hole and the feeding blind hole.
The feeding groove on the front mold core is communicated with the tail fin bottom plate cavity through a connecting groove; the feeding groove on the rear mold core is only communicated with the feeding blind hole.
Furthermore, the length of the connecting groove is not less than half of the maximum length of the slag discharging cavity.
The slag discharging cavities arranged on the front mold core and the rear mold core are opposite to each other, the number of the slag discharging cavities is 5, and the slag discharging cavities are uniformly arranged on the outer side of the tail fin bottom plate cavity.
The second positioning through hole and the second tail connecting pipe core are of a step hole and a step shaft structure which are matched with each other.
A feeding positioning hole with an arc-shaped structure is arranged at the side end of the front mold core; the feeding assembly comprises an arc-shaped table, one side of the arc-shaped table is matched with the feeding positioning hole of the arc-shaped structure; a feeding sleeve is arranged at one end of the arc-shaped table; and a gap exists between the inner wall of the feeding sleeve and the arc-shaped platform.
Ejector rod through holes are formed in the middle of each slag discharging cavity in the rear mold core, between any two blade cavities and on the feeding groove.
The first tail connecting pipe core comprises a sleeve inserted into the first positioning through hole, and a solid straight pipe in a step structure is further mounted at the other end of the sleeve.
The utility model discloses beneficial effect:
the utility model designs a die-casting die aiming at the aircraft empennage with a complex cavity structure, which uses a front template and a rear template, respectively sets a feeding through hole and a feeding blind hole, and installs a front mold core and a rear mold core through a mold core installation cavity; a tail fin bottom plate cavity is arranged on the front mold core; a blade cavity is arranged on the rear mold core; the installation of the first empennage connecting pipe core and the second empennage connecting pipe core is completed through the first positioning through hole and the second positioning through hole on the front mold core and the rear mold core, so that the arrangement of an empennage connecting pipe cavity is realized; the feeding assembly and the corresponding pipeline structure are further arranged, the slag discharging cavity is arranged for discharging slag, and finally the formed part is taken down by arranging the ejector rod through the ejector rod perforation and the ejector rod, so that the problems that the difficulty of machining the tail wing of the aircraft by adopting other modes is high, the cost is high and the machining condition is harsh at present are effectively solved.
Drawings
FIG. 1 is a schematic three-dimensional view of the rear wing of the aircraft to be machined in the present example;
figure 2 is an exploded view of the assembly of the inventive apparatus of this embodiment;
FIG. 3 is a schematic three-dimensional structure of the rear mold plate in the present embodiment;
FIG. 4 is a schematic three-dimensional structure of the front core in the present embodiment;
FIG. 5 is a schematic three-dimensional structure of the rear core in the present embodiment;
FIG. 6 is a schematic three-dimensional structure of a first tail connecting pipe core in the present embodiment;
FIG. 7 is a schematic three-dimensional structure of a second fin connecting core in the present embodiment;
FIG. 8 is a schematic three-dimensional structure of the feeding block of the present embodiment;
description of reference numerals: 1. front mould board, 1A, feed through hole, 2, back template, 2A, the feeding blind hole, 3, the mold core installation cavity, 4, preceding mold core, 4A, fin bottom plate die cavity, 4B, second positioning hole, 4C, the feeding locating hole, 5, back mold core, 5A, the blade die cavity, 5B, first positioning hole, 6, the feed chute, 7, first fin is managed the core even, 8, second fin is managed the core even, 9, the ejector pin is perforated, 10, the ejector pin, 11, the feeding subassembly, 11A, the arc platform, 11B, the feeding sleeve pipe, P1, arrange the sediment chamber.
Detailed Description
The invention will be further described with reference to the following drawings and specific embodiments:
example (b):
referring to fig. 2 to 8, the embodiment provides a die-casting mold for processing a empennage of a small aircraft, which comprises a front template 1 and a rear template 2 which are matched; a mold core mounting cavity 3 with a square structure is formed in the middle of two side end faces of the front mold plate 1 and the rear mold plate 2 which are opposite; the front template 1 and the rear template 2 are also provided with a feeding through hole 1A and a feeding blind hole 2A which are opposite to each other and communicated with the die core mounting cavity 3; a front mold core 4 and a rear mold core 5 which are matched with each other are detachably arranged in the mold core mounting cavity 3; two empennage bottom plate cavities 4A with the same structure are arranged on the side end surface of the front mold core 4 opposite to the rear mold core 5; the slag discharge cavity P1 is arranged on the front mold core 4 and the rear mold core 5 at the position close to the peripheral side of the empennage base plate cavity 4A, and the front mold core 4 and the rear mold core 5 are both provided with a feed chute 6; the feed chute 6 is in a Y-shaped structure, and two ends of the feed chute 6 on the front mold core 4 are respectively communicated with the two empennage base plate cavities 4A; the two feeding grooves 6 are respectively communicated with the feeding through hole 1A and the feeding blind hole 2A; a blade cavity 5A with a blind hole structure is further formed in the position, connected with the empennage base plate cavity 4A, of the rear mold core 5 along the thickness direction of the rear mold core, and in the embodiment, the blade cavity 5A consists of 8 independent blades; a first positioning through hole 5B is formed in the middle of the tail fin bottom plate cavity 4A, and a second positioning through hole 4B is formed in the position, opposite to the first positioning through hole 5B, of the front mold core 4; the first tail connecting pipe core 7 and the second tail connecting pipe core 8 are arranged by penetrating through the first positioning through hole 5B and the second positioning through hole 4B respectively, the first tail connecting pipe core 7 is of a sleeve structure, and the second tail connecting pipe core 8 is of a straight solid pipe structure matched with the sleeve structure; a mandril through hole 9 is arranged at the corresponding position of the rear mold core 5 and the rear mold plate 2; the mandril 10 passes through the mandril through hole 9 and is detachably arranged on the rear template 2; and a feeding assembly 11 is also arranged on the feeding through hole 1A and the feeding blind hole 2A.
A feeding groove 6 on the front mold core 4 is communicated with a tail fin bottom plate cavity 4A through a connecting groove; the feeding groove 6 on the rear mold core 4 is only communicated with the feeding blind hole 2A. In order to ensure the precision of the die-casting molding empennage, a bottom plate of the empennage, blades of the empennage and two most cavities of a connecting pipe are respectively arranged on a front mold core 4 and a rear mold core 5; meanwhile, the connecting structure of the feeding chute on the rear mold core is arranged so that materials introduced into the cavity can enter the space between the blade cavity 5A on the rear mold core and the connecting pipe cavity defined by the first positioning through hole 5B and the second positioning through hole 4B along the cavity 4A of the tail fin bottom plate on the front mold core 4.
Further, the length of the connecting groove is not less than half of the maximum length of the slag discharge cavity P1. Ejector pin through holes 9 are formed in the middle of each slag discharge cavity P1 on the rear mold core 5, the position between any two blade cavities 5A and the feed chute 6. The large connecting groove and the uniform arrangement of the ejector pin through holes 9 are to ensure that the ejector pin arranged at the slag discharge opening P1 is not broken from the connecting groove during feeding when the ejector pin is used for ejecting the formed tail structure, thereby improving the reliability of operation.
The slag discharge cavities P1 arranged on the front mold core 4 and the rear mold core 5 are opposite to each other, and the number of the slag discharge cavities P1 is 5, and the slag discharge cavities P1 are uniformly arranged on the outer side of the tail fin bottom plate cavity 4A.
The second positioning through hole 4B and the second tail connecting pipe core 8 are of a step hole and a step shaft structure which are matched with each other. The second positioning through hole 4B and the second tail connecting pipe core 8 which are matched in a step structure can prevent the second tail connecting pipe core 8 from falling into the second positioning through hole 4B, so that the taking-out difficulty is increased. Similarly, the first tail connecting pipe core 7 is inserted into the first positioning through hole 5B sleeve, the other end of the sleeve is provided with a solid straight pipe in a step structure, and the structure arrangement can also play a similar role.
A feeding positioning hole 4C with an arc structure is arranged at the side end of the front mold core 4; the feeding component 11 comprises an arc-shaped table 11A, one side of which is matched with the feeding positioning hole 4C of the arc-shaped structure; a feeding sleeve 11B is arranged at one end of the arc-shaped table 11A; and a gap exists between the inner wall of the feed sleeve 11B and the arc-shaped table 11A. The gap is mainly for the convenience of material flow into the feed chute, while the feed assembly 11 of the separation structure is for the assurance of its removal.
When using this embodiment utility model discloses device aircraft fin when die-casting shaping, can refer to following step:
s1, folding the front mold core 4 and the rear mold core 5;
s2, placing the folded front mold core 4 and the folded rear mold core 5 into the rear mold plate 2; wherein the lower bottom surface of the rear mold core 5 is attached to the inner bottom surface of the mold core mounting cavity 3 of the rear mold plate 2; the feeding assembly 11 is assembled and then placed in the feeding blind hole 2A;
s3, mounting the second tail wing connecting pipe core 8 on the second positioning through hole 4B, and then folding and locking the front template 1 and the rear template 2;
s4, mounting the first tail connecting pipe core 7 in the first positioning through hole 5B, and fixing the ejector rod 10 after penetrating through the ejector rod through hole 9;
s5, introducing materials along the feed through hole 1A on the front template 1 for die casting;
and S6, opening the die after die casting is finished, and ejecting the formed empennage device by using the ejector rod 10 to finish the die casting.
Claims (8)
1. A die casting die for processing a small aircraft empennage comprises a front template (1) and a rear template (2) which are matched with each other; the middle parts of two side end surfaces of the front template (1) and the rear template (2) which are opposite are provided with a mold core mounting cavity (3) with a square structure; the method is characterized in that: a feeding through hole (1A) and a feeding blind hole (2A) which are opposite to each other and communicated with the die core mounting cavity (3) are also formed on the front die plate (1) and the rear die plate (2); a front mold core (4) and a rear mold core (5) which are matched with each other are detachably arranged in the mold core mounting cavity (3); a tail fin bottom plate cavity (4A) is formed in the side end face, opposite to the rear mold core (5), of the front mold core (4); the slag discharge cavity (P1) is arranged at the position of the front mold core (4) and the rear mold core (5) close to the peripheral side of the tail fin bottom plate cavity (4A), and the front mold core (4) and the rear mold core (5) are both provided with a feed chute (6); the feeding groove (6) is respectively communicated with the feeding through hole (1A) and the feeding blind hole (2A); a blade cavity (5A) with a blind hole structure is further formed in the position, connected with the empennage base plate cavity (4A), of the rear mold core (5) along the thickness direction of the rear mold core, a first positioning through hole (5B) is formed in the middle of the empennage base plate cavity (4A), and a second positioning through hole (4B) is formed in the position, opposite to the first positioning through hole (5B), of the front mold core (4); the first tail connecting pipe core (7) and the second tail connecting pipe core (8) respectively penetrate through the first positioning through hole (5B) and the second positioning through hole (4B), the first tail connecting pipe core (7) is of a sleeve structure, and the second tail connecting pipe core (8) is of a straight solid pipe structure matched with the sleeve structure; a mandril through hole (9) is arranged at the corresponding position of the rear mold core (5) and the rear mold plate (2); the ejector rod (10) passes through the ejector rod through hole (9) and is detachably arranged on the rear template (2); and a feeding assembly (11) is also arranged on the feeding through hole (1A) and the feeding blind hole (2A).
2. The die casting mold for machining the empennage of the small aircraft as claimed in claim 1, wherein: a feeding groove (6) on the front mold core (4) is communicated with the tail fin bottom plate cavity (4A) through a connecting groove; the feeding groove (6) on the rear mold core (5) is only communicated with the feeding blind hole (2A).
3. The die casting mold for machining the empennage of the small aircraft as claimed in claim 2, wherein: the length of the connecting groove is not less than half of the maximum length of the slag discharge cavity (P1).
4. The die casting mold for machining the empennage of the small aircraft as claimed in claim 1, wherein: the slag discharge cavities (P1) arranged on the front mold core (4) and the rear mold core (5) are opposite to each other, the number of the slag discharge cavities is 5, and the slag discharge cavities are uniformly arranged on the outer side of the tail fin bottom plate cavity (4A).
5. The die casting mold for machining the empennage of the small aircraft as claimed in claim 1, wherein: the second positioning through hole (4B) and the second tail connecting pipe core (8) are of a step hole and step shaft structure which are matched with each other.
6. The die casting mold for machining the empennage of the small aircraft as claimed in claim 1, wherein: a feeding positioning hole (4C) with an arc-shaped structure is formed in the side end of the front mold core (4); the feeding assembly (11) comprises an arc-shaped table (11A) with one side matched with the feeding positioning hole (4C) of the arc-shaped structure; a feeding sleeve (11B) is arranged at one end of the arc-shaped table (11A); and a gap is formed between the inner wall of the feeding sleeve (11B) and the arc-shaped platform (11A).
7. The die casting mold for machining the empennage of the small aircraft as claimed in claim 1, wherein: ejector rod through holes (9) are formed in the middle of each slag discharge cavity (P1) on the rear mold core (5), between any two blade cavities (5A) and on the feeding groove (6).
8. The die casting mold for machining the empennage of the small aircraft as claimed in claim 1, wherein: the first tail connecting pipe core (7) comprises a sleeve inserted into the first positioning through hole (5B), and the other end of the sleeve is also provided with a solid straight pipe in a step structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921796780.XU CN211101508U (en) | 2019-10-24 | 2019-10-24 | Die casting die for machining empennage of small aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921796780.XU CN211101508U (en) | 2019-10-24 | 2019-10-24 | Die casting die for machining empennage of small aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN211101508U true CN211101508U (en) | 2020-07-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921796780.XU Active CN211101508U (en) | 2019-10-24 | 2019-10-24 | Die casting die for machining empennage of small aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756769A (en) * | 2019-10-24 | 2020-02-07 | 贵州裕高电子有限责任公司 | Die-casting die for machining empennage of small aircraft and using method of die-casting die |
-
2019
- 2019-10-24 CN CN201921796780.XU patent/CN211101508U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756769A (en) * | 2019-10-24 | 2020-02-07 | 贵州裕高电子有限责任公司 | Die-casting die for machining empennage of small aircraft and using method of die-casting die |
| CN110756769B (en) * | 2019-10-24 | 2023-12-29 | 贵州裕高电子有限责任公司 | Die casting die for processing tail fin of small aircraft and using method thereof |
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