CN212046066U - A shaping cutting die for production of aviation combined material part - Google Patents
A shaping cutting die for production of aviation combined material part Download PDFInfo
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- CN212046066U CN212046066U CN201922453488.4U CN201922453488U CN212046066U CN 212046066 U CN212046066 U CN 212046066U CN 201922453488 U CN201922453488 U CN 201922453488U CN 212046066 U CN212046066 U CN 212046066U
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- mounting frame
- cutting die
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- cylinder
- face plate
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- 238000005520 cutting process Methods 0.000 title claims abstract description 39
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 11
- 239000000463 material Substances 0.000 title abstract description 11
- 238000007493 shaping process Methods 0.000 title abstract description 9
- 238000007731 hot pressing Methods 0.000 claims abstract description 15
- 239000002131 composite material Substances 0.000 claims description 17
- 230000007306 turnover Effects 0.000 claims description 12
- 150000001875 compounds Chemical class 0.000 abstract description 5
- 238000003860 storage Methods 0.000 abstract 1
- 230000007423 decrease Effects 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
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Abstract
The utility model discloses a shaping cutting die for production of compound material part of aviation, the on-line screen storage device comprises a base, the upper end of base is equipped with two lift cylinder, two lift cylinder sets up respectively in the both sides of base, two lift cylinder's equal vertical up and the same installing frame of fixedly connected with of piston end, set up the returning face plate in the installing frame, the returning face plate, the upper and lower both sides of returning face plate are equipped with cutting die head, last hot pressing die respectively, the base upper end is equipped with the lower mould that corresponds with last hot pressing die, the equal fixedly connected with pivot in both ends of returning face plate, and the pivot rotates and connect on the installing frame inner wall, be equipped with the tilting mechanism that is used for driving the returning face plate upset on the lateral wall of installing frame. The utility model discloses with hot briquetting and finished product cutting integrated design, production efficiency is high, and the shaping material carries out the cutting of hot in the heat, and hot briquetting, cutting stability are high, improve the product quality.
Description
Technical Field
The utility model relates to an aviation compound material part production technical field especially relates to a shaping cutting die for production of aviation compound material part.
Background
Aerospace composites are widely used, the main benefits of composites are reduced weight and simpler assembly, and performance advantages and reduced aircraft structural weight are the primary drivers of composite development in military aircraft.
In the production of aviation composite material parts, generally, fiber/fabric composite materials are hot-pressed and molded on the parts through hot-pressing glue to form the composite materials, and the composite materials after composite molding need to be cut to remove redundant rim charge, but in the existing cutting step, because the cutting difficulty is increased in cold cutting, cutting burrs are easily generated, the production efficiency is reduced, and the generated burrs make the product quality not good enough.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the defects existing in the prior art and providing a forming and cutting die for producing aviation composite parts.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a shaping cutting die for production of compound material part of aviation, includes the base, the upper end of base is equipped with two lift cylinder, two lift cylinder sets up respectively in the both sides of base, two lift cylinder's equal vertical up and the same installing frame of fixedly connected with of piston end, set up the returning face plate in the installing frame, the returning face plate, the upper and lower both sides of returning face plate are equipped with cutting die head, last hot pressing mould respectively, the base upper end is equipped with the lower mould that corresponds with last hot pressing mould, the equal fixedly connected with pivot in both ends of returning face plate, and the pivot rotates and connect on the installing frame inner wall, be equipped with the tilting mechanism that is used for driving the returning face plate upset on the lateral wall of installing frame, be equipped with the locking mechanism who is used for fixed returning face plate on.
Preferably, the turnover mechanism comprises a first cylinder fixedly mounted on the outer wall of the mounting frame, a piston end of the first cylinder penetrates through the mounting frame and is fixedly connected with a rack, a gear is fixedly sleeved on the rotating shaft, and the gear is meshed with the rack.
Preferably, locking mechanism includes the second cylinder of fixed mounting on the installing frame outer wall, the piston end of second cylinder runs through the installing frame and fixedly connected with fitting pin, be equipped with the locking hole that corresponds with the fitting pin on the lateral wall of returning face plate.
Preferably, be equipped with spacing spout on the inner wall of installing frame, the one end that first cylinder was kept away from to the rack is equipped with limiting slide block, limiting slide block sliding connection is in spacing spout.
Preferably, the limiting sliding block and the limiting sliding groove are of T-shaped structures matched with each other.
Preferably, the limiting slide block and the rack are integrally formed.
The utility model has the advantages that:
through setting up tilting mechanism, the cutting die head, after accomplishing hot briquetting through last hot pressing mould and lower mould cooperation, it rises to start lift cylinder, start the shrink of second cylinder, make the fitting pin extract the locking hole, the extension of restart first cylinder, and then drive the rack and remove, because rack and gear engagement, and then drive gear rotates, it rotates to drive the pivot, and then drive the upset of returning face plate, make the cutting die head rotate to the below, it makes the fitting pin insert the downthehole locking of returning face plate fixed to restart second cylinder extension, start lift cylinder decline, it cuts to drive the shaping material on the lower mould to drive the cutting die head decline, cutting efficiency is higher, and can effectively avoid the burr that the cold-cutting produced.
Through setting up locking mechanism, start the extension of second cylinder and make the fitting pin insert the downthehole locking of upset board fixed, and then guarantee the stability when hot briquetting, cutting, improve the product quality.
Drawings
Fig. 1 is a schematic structural view of a forming and cutting die for producing an aviation composite part according to the present invention;
fig. 2 is a schematic top view of a mounting frame of a forming and cutting die for producing an aviation composite material part according to the present invention;
fig. 3 is an enlarged view of a portion a in fig. 2.
In the figure: the device comprises a base 1, a lower die 2, a lifting oil cylinder 3, an upper hot-pressing die 4, a mounting frame 5, a first air cylinder 6, a second air cylinder 7, a turnover plate 8, a cutting die head 9, a rack 10, a limiting sliding groove 11, a limiting sliding block 12, a locking pin 13, a rotating shaft 14 and a gear 15.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Referring to fig. 1-3, a shaping cutting die for production of aviation compound material part, including base 1, the upper end of base 1 is equipped with two lift cylinder 3, two lift cylinder 3 set up respectively in the both sides of base 1, the equal vertical upper and same installing frame 5 of fixedly connected with of piston end of two lift cylinder 3, set up returning face plate 8 in the installing frame 5, returning face plate 8's upper and lower both sides are equipped with cutting die head 9 respectively, go up hot pressing die 4, the base 1 upper end is equipped with the lower mould 2 that corresponds with last hot pressing die 4, the equal fixedly connected with pivot 14 in both ends of returning face plate 8, and pivot 14 rotates and connects on 5 inner walls of installing frame, be equipped with the tilting mechanism that is used for driving returning face plate 8 upset on the lateral wall of installing frame 5, be equipped with the locking mechanism that is used for fixed returning face plate.
The utility model discloses in, tilting mechanism includes first cylinder 6 of fixed mounting on the 5 outer walls of installing frame, and the piston end of first cylinder 6 runs through installing frame 5 and fixedly connected with rack 10, and the fixed gear 15 that has cup jointed in the pivot 14, and gear 15 and rack 10 mesh.
Specifically, locking mechanism includes second cylinder 7 of fixed mounting on the 5 outer walls of installing frame, and the piston end of second cylinder 7 runs through installing frame 5 and fixedly connected with fitting pin 13, is equipped with the locking hole that corresponds with fitting pin 13 on the lateral wall of returning face plate 8, starts the extension of second cylinder 7 and makes fitting pin 13 insert locking downthehole with returning face plate 8 locking fixed, and then guarantees hot briquetting, stability when cutting, improves the product quality.
Specifically, be equipped with spacing spout 11 on the inner wall of installing frame 5, the one end that first cylinder 6 was kept away from to rack 10 is equipped with limit slider 12, limit slider 12 sliding connection is in spacing spout 11, slide in spacing spout 11 through limit slider 12, and then carry out spacing direction to rack 10's removal, make the accuracy of rack 10 removal stable, limit slider 12 and limit spout 11 are the T type structure of mutual adaptation, it is more stable to slide, and then spacing, the direction is more accurate stable. Limiting slide block 12 and rack 10 integrated into one piece, structural strength is higher, and the durability is better.
When the utility model is used, the material part to be compounded is arranged on the lower die 2, the lifting oil cylinder 3 is started to descend to drive the upper hot-pressing die 4 to press downwards, the upper hot-pressing die 4 is matched with the lower die 2 to complete hot-pressing molding, after the hot pressing is completed, the lifting oil cylinder 3 is started to ascend, the second air cylinder 7 is started to contract, so that the locking pin 13 is pulled out of the locking hole, and then the first cylinder 6 is started to extend, thereby driving the rack 10 to move, since the rack 10 is engaged with the gear 15, and the gear 15 is driven to rotate, the rotating shaft 14 is driven to rotate, and then drive 8 upsets of returning face plate for cutting die head 9 changes to the below, and the extension of restart second cylinder 7 makes the fitting pin 13 insert the downthehole 8 locks the returning face plate fixedly of locking, starts lift cylinder 3 and descends, drives cutting die head 9 and descends and carry out the cutting of hot in the shaping material on lower mould 2, and cutting efficiency is higher, and can effectively avoid the burr that cold cutting produced.
Above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the design of the present invention, equivalent replacement or change should be covered within the protection scope of the present invention.
Claims (6)
1. The forming and cutting die for producing aviation composite parts comprises a base (1) and is characterized in that two lifting oil cylinders (3) are arranged at the upper end of the base (1), the two lifting oil cylinders (3) are respectively arranged at two sides of the base (1), the piston ends of the two lifting oil cylinders (3) are vertically upward and fixedly connected with the same mounting frame (5), a turnover plate (8) is arranged in the mounting frame (5), the turnover plate (8) is arranged at the upper side and the lower side of the turnover plate (8) and is respectively provided with a cutting die head (9) and an upper hot pressing die (4), a lower die (2) corresponding to the upper hot pressing die (4) is arranged at the upper end of the base (1), rotating shafts (14) are fixedly connected at two ends of the turnover plate (8), the rotating shafts (14) are rotatably connected on the inner wall of the mounting frame (5), and a turnover mechanism for driving the turnover plate (8) to turn over is arranged on the outer side wall of the mounting frame, and a locking mechanism for fixing the turnover plate (8) is arranged on the outer side wall of the mounting frame (5).
2. The forming and cutting die for producing aviation composite parts as claimed in claim 1, wherein the turnover mechanism comprises a first cylinder (6) fixedly mounted on the outer wall of the mounting frame (5), a piston end of the first cylinder (6) penetrates through the mounting frame (5) and is fixedly connected with a rack (10), a gear (15) is fixedly sleeved on the rotating shaft (14), and the gear (15) is meshed with the rack (10).
3. The forming and cutting die for producing aviation composite parts according to claim 1, wherein the locking mechanism comprises a second cylinder (7) fixedly mounted on the outer wall of the mounting frame (5), the piston end of the second cylinder (7) penetrates through the mounting frame (5) and is fixedly connected with a locking pin (13), and a locking hole corresponding to the locking pin (13) is formed in the side wall of the turnover plate (8).
4. The forming and cutting die for producing aviation composite parts according to claim 2, wherein a limiting sliding groove (11) is formed in the inner wall of the mounting frame (5), a limiting sliding block (12) is arranged at one end, away from the first air cylinder (6), of the rack (10), and the limiting sliding block (12) is connected in the limiting sliding groove (11) in a sliding mode.
5. The forming and cutting die for producing aviation composite parts according to claim 4, wherein the limiting slide block (12) and the limiting slide groove (11) are of mutually matched T-shaped structures.
6. The forming and cutting die for the production of aeronautical composite parts according to claim 4, characterized in that the limiting slider (12) is integrally formed with the toothed rack (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922453488.4U CN212046066U (en) | 2019-12-31 | 2019-12-31 | A shaping cutting die for production of aviation combined material part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922453488.4U CN212046066U (en) | 2019-12-31 | 2019-12-31 | A shaping cutting die for production of aviation combined material part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212046066U true CN212046066U (en) | 2020-12-01 |
Family
ID=73535241
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922453488.4U Active CN212046066U (en) | 2019-12-31 | 2019-12-31 | A shaping cutting die for production of aviation combined material part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212046066U (en) |
-
2019
- 2019-12-31 CN CN201922453488.4U patent/CN212046066U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210209 Address after: 710000 Jingpu Road, Jinghe Industrial Park, Xi'an City, Shaanxi Province Patentee after: Xi'an yinglike Electric Technology Co.,Ltd. Address before: No. 1201, Huanhu West Road, Longzihu District, Bengbu City, Anhui Province 233060 Patentee before: Wang Li |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A Forming and Cutting Die for the Production of Aircraft Composite Parts Effective date of registration: 20220929 Granted publication date: 20201201 Pledgee: Xi'an Gaoling Sanyang Financing Guarantee Co.,Ltd. Pledgor: Xi'an yinglike Electric Technology Co.,Ltd. Registration number: Y2022610000638 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Granted publication date: 20201201 Pledgee: Xi'an Gaoling Sanyang Financing Guarantee Co.,Ltd. Pledgor: Xi'an yinglike Electric Technology Co.,Ltd. Registration number: Y2022610000638 |