CN204052857U - A kind of aircraft cabin body vertical slitting gate system - Google Patents
A kind of aircraft cabin body vertical slitting gate system Download PDFInfo
- Publication number
- CN204052857U CN204052857U CN201420474818.2U CN201420474818U CN204052857U CN 204052857 U CN204052857 U CN 204052857U CN 201420474818 U CN201420474818 U CN 201420474818U CN 204052857 U CN204052857 U CN 204052857U
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- vertical
- cabin body
- vertical tube
- base plate
- gate system
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- 238000005266 casting Methods 0.000 claims abstract description 18
- 238000002347 injection Methods 0.000 abstract description 3
- 239000007924 injection Substances 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- IXSZQYVWNJNRAL-UHFFFAOYSA-N etoxazole Chemical compound CCOC1=CC(C(C)(C)C)=CC=C1C1N=C(C=2C(=CC=CC=2F)F)OC1 IXSZQYVWNJNRAL-UHFFFAOYSA-N 0.000 description 1
- 230000003031 feeding effect Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The utility model provides a kind of aircraft cabin body vertical slitting gate system, comprises cabin body, vertical seam, vertical tube, base plate, support column; Described cabin body is cylindric; Described vertical tube is uniformly distributed around cabin portion outside, and be connected by vertical seam the isometric with cabin body between vertical tube and cabin body, cabin body is longer than in vertical tube lower end; Described base plate is square shaft-like, with cabin body concentric, with vertical tube with distributing, to be connected to bottom vertical tube and to cover the bottom of vertical tube; Described support column is vertically set on base plate circle centre position, base plate is fixed by bottom base plate.The utility model is by unique injection system structure and parameter, for aircraft cabin body vertical slitting gate system provides a set of comparatively ripe scheme, efficiently solve taller and bigger to casting structure for aircraft cabin body in prior art, that shape is cylindrical shape Shell-Class, cast-internal dense structure degree, mechanical performance and air-tightness and require the higher difficult problem not easily realized.
Description
Technical field
The utility model relates to a kind of aircraft cabin body vertical slitting gate system.
Background technology
The shell of aircraft---cabin body, complex structure, internal soundness requires high, mostly is I class foundry goods and above requirement.For thin-walled, baroque tall and big cabin body class foundry goods, counter-pressure casting is adopted to be the first-selected technique ensureing foundry goods at present.Counter-pressure casting technique is the antigravity accurate forming method of a kind of advanced person, and this method comes from low pressure casting, and it has the feature of low pressure casting and autoclave pressure casting concurrently.Counter-pressure casting process is advanced, and high financial profit is applied widely, is applicable to various casting mold.For large thin-wall cabin body foundry goods, although adopt counter-pressure casting technology, but, in order to fill type steadily and obtain compact tissue, must ensure that foundry goods solidifies and crystallization under stress in order, running gate system is often designed to vertical Slot Gating System, but does not provide ripe technical scheme for the vertical slitting gate system of aircraft cabin body in prior art.
Utility model content
For solving the problems of the technologies described above, the utility model provides a kind of aircraft cabin body vertical slitting gate system, this aircraft cabin body vertical slitting gate system is by unique injection system structure and parameter, for aircraft cabin body vertical slitting gate system provides a set of comparatively ripe scheme, efficiently solve taller and bigger to casting structure for aircraft cabin body in prior art, that shape is cylindrical shape Shell-Class, cast-internal dense structure degree, mechanical performance and air-tightness and require the higher difficult problem not easily realized.
The utility model is achieved by the following technical programs.
A kind of aircraft cabin body vertical slitting gate system that the utility model provides, comprises cabin body, vertical seam, vertical tube, base plate, support column; Described cabin body is cylindric; Described vertical tube is uniformly distributed around cabin portion outside, and be connected by vertical seam the isometric with cabin body between vertical tube and cabin body, cabin body is longer than in vertical tube lower end; Described base plate is square shaft-like, with cabin body concentric, with vertical tube with distributing, to be connected to bottom vertical tube and to cover the bottom of vertical tube; Described support column is vertically set on base plate circle centre position, base plate is fixed by bottom base plate.
The quantity of described vertical seam or vertical tube meets one of following condition:
1.
wherein n is quantity, and P is foundry goods gabarit girth, and δ is vertical seam thickness;
2.
wherein n is quantity, and P is foundry goods gabarit girth, and L is feeding distance, L=100 ~ 220mm.
The thickness of described vertical seam meets following condition:
Connor gate place casting section thickness is a, and the thickness of vertical seam is δ:
During a >=10, get δ=(0.8 ~ 1) a;
During a < 10, get δ=(1 ~ 1.5) a.
The length of described cabin body or vertical seam is 20 ~ 40mm.
The diameter of described vertical tube is 4 ~ 6 times of described vertical seam thickness.
The beneficial effects of the utility model are: by injection system structure and the parameter of uniqueness, for aircraft cabin body vertical slitting gate system provides a set of comparatively ripe scheme, efficiently solve taller and bigger to casting structure for aircraft cabin body in prior art, that shape is cylindrical shape Shell-Class, cast-internal dense structure degree, mechanical performance and air-tightness and require the higher difficult problem not easily realized.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
In figure: the body of 1-cabin, the vertical seam of 2-, 3-vertical tube, 4-base plate, 5-support column.
Detailed description of the invention
Further describe the technical solution of the utility model below, but described in claimed scope is not limited to.
A kind of aircraft cabin body vertical slitting gate system as shown in Figure 1, comprises cabin body 1, vertical seam 2, vertical tube 3, base plate 4, support column 5; Described cabin body 1 is cylindric; Described vertical tube 3 is uniformly distributed outside cabin body 1, and be connected by the vertical seam 2 isometric with cabin body 1 between vertical tube 3 and cabin body 1, cabin body 1 is longer than in vertical tube 3 lower end; Described base plate 4 is square shaft-like, with cabin body 1 concentric, with vertical tube 3 with distributing, to be connected to bottom vertical tube 3 and to cover the bottom of vertical tube 3; Described support column 5 is vertically set on base plate 4 circle centre position, base plate 4 is fixed by bottom base plate 4.
The quantity of vertical seam should determine according to the height of the technical requirement of the external wide girth in cabin and foundry goods, and cabin body casting techniques requires high, and vertical quantity of stitching can design some more.In addition, also should consider that (quantity is many, and running channel not easily cuts removal) are removed in the cutting of running channel.Generally, can be undertaken calculating (rounding up when result of calculation is decimal) by following formula:
wherein n is quantity, and P is foundry goods gabarit girth, and δ is vertical seam thickness;
In addition, the feeding distance of cabin body foundry goods vertical slitting gate system is at 100 ~ 220 (mm), and consider the cutting of running channel and uniform etc., the quantity of vertical seam also can be carried out calculating (rounding up when result of calculation is decimal) by following formula:
wherein n is quantity, and P is foundry goods gabarit girth, and L is feeding distance, L=100 ~ 220mm.
The thickness of described vertical seam 2 meets following condition:
Connor gate place casting section thickness is a, and the thickness of vertical seam 2 is δ:
During a >=10, get δ=(0.8 ~ 1) a;
During a < 10, get δ=(1 ~ 1.5) a.
Sometimes, for guiding thermal center into vertical tube 3, desirable δ=(1.5 ~ 2) a, and consider to place suitable iron chill shock chilling on opposite, gap.When casting techniques requires low, desirable smaller value, when requiring high, then desirable higher value.
The length of described cabin body 1 or vertical seam 2 is 20 ~ 40mm.Length is too short at vertical seam 2 place is easy to occur overheated, oversize, and vertical tube 3 feeding effect can reduce again.
The diameter of described vertical tube 3 is 4 ~ 6 times of described vertical seam 2 thickness.
Slot Gating System, in Al alloys andMg alloys castings production, obtains and applies more and more widely, and shows it to the special-effect improving Internal Quality of Cast.The technical scheme that this patent provides is taller and bigger to casting structure, shape is cylindric Shell-Class, cast-internal dense structure degree, mechanical performance and air-tightness require that higher foundry goods is more applicable, should note during the design of gap running channel with chill with the use of, bottom foundry goods, place chill, the effect of gap running gate system can be given full play to.
Claims (5)
1. an aircraft cabin body vertical slitting gate system, it is characterized in that: comprise cabin body (1), vertical seam (2), vertical tube (3), base plate (4), support column (5), described cabin body (1) is cylindric; Described vertical tube (3) is uniformly distributed around cabin body (1) outside, be connected by the vertical seam (2) isometric with cabin body (1) between vertical tube (3) and cabin body (1), cabin body (1) is longer than in vertical tube (3) lower end; Described base plate (4), for square shaft-like, with cabin body (1) concentric, with vertical tube (3) with distribute, be connected to bottom vertical tube (3) and cover the bottom of vertical tube (3); Described support column (5) is vertically set on base plate (4) circle centre position, base plate (4) is fixed by base plate (4) bottom.
2. aircraft cabin as claimed in claim 1 body vertical slitting gate system, is characterized in that: the quantity of described vertical seam (2) or vertical tube (3) meets one of following condition:
1.
wherein n is quantity, and P is foundry goods gabarit girth, and δ is vertical seam thickness;
2.
wherein n is quantity, and P is foundry goods gabarit girth, and L is feeding distance, L=100 ~ 220mm.
3. aircraft cabin as claimed in claim 1 body vertical slitting gate system, is characterized in that: the thickness of described vertical seam (2) meets following condition:
Connor gate place casting section thickness is a, and the thickness of vertical seam (2) is δ:
During a >=10, get δ=(0.8 ~ 1) a;
During a < 10, get δ=(1 ~ 1.5) a.
4. aircraft cabin as claimed in claim 1 body vertical slitting gate system, is characterized in that: the length of described cabin body (1) or vertical seam (2) is 20 ~ 40mm.
5. aircraft cabin as claimed in claim 1 body vertical slitting gate system, is characterized in that: the diameter of described vertical tube (3) is 4 ~ 6 times of described vertical seam (2) thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420474818.2U CN204052857U (en) | 2014-08-21 | 2014-08-21 | A kind of aircraft cabin body vertical slitting gate system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420474818.2U CN204052857U (en) | 2014-08-21 | 2014-08-21 | A kind of aircraft cabin body vertical slitting gate system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204052857U true CN204052857U (en) | 2014-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420474818.2U Expired - Fee Related CN204052857U (en) | 2014-08-21 | 2014-08-21 | A kind of aircraft cabin body vertical slitting gate system |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107876736A (en) * | 2017-12-29 | 2018-04-06 | 洛阳乾中新材料科技有限公司 | Counter-pressure casting pouring gate structure and the casting counter-pressure casting method with the pouring gate structure |
| CN109848370A (en) * | 2019-04-03 | 2019-06-07 | 洛阳乾中新材料科技有限公司 | A kind of sand casting casting external form moulding tooling |
| CN109854596A (en) * | 2019-03-08 | 2019-06-07 | 北京航天自动控制研究所 | A kind of aircraft optical dome and cabin location and installation equipment and installation method |
| CN110180996A (en) * | 2019-07-03 | 2019-08-30 | 陈健美 | A kind of method cracked in elimination gravitational casting |
| CN110681845A (en) * | 2019-08-28 | 2020-01-14 | 贵州航天风华精密设备有限公司 | Cabin gap pouring structure |
| CN112427608A (en) * | 2020-11-30 | 2021-03-02 | 贵州航天风华精密设备有限公司 | Large magnesium alloy special-shaped structural part casting die and process |
| CN113102690A (en) * | 2021-04-06 | 2021-07-13 | 洛阳乾中新材料科技有限公司 | Design method of casting mold |
| CN115401169A (en) * | 2022-08-30 | 2022-11-29 | 贵州安吉航空精密铸造有限责任公司 | Process method for filling large high-temperature alloy thin-wall casing support plate |
| CN118162587A (en) * | 2024-05-14 | 2024-06-11 | 贵州航天风华精密设备有限公司 | Sand casting molding device and casting method for special-shaped thin-wall castings |
-
2014
- 2014-08-21 CN CN201420474818.2U patent/CN204052857U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107876736A (en) * | 2017-12-29 | 2018-04-06 | 洛阳乾中新材料科技有限公司 | Counter-pressure casting pouring gate structure and the casting counter-pressure casting method with the pouring gate structure |
| CN109854596A (en) * | 2019-03-08 | 2019-06-07 | 北京航天自动控制研究所 | A kind of aircraft optical dome and cabin location and installation equipment and installation method |
| CN109854596B (en) * | 2019-03-08 | 2021-02-09 | 北京航天自动控制研究所 | A kind of aircraft optical head cover and cabin positioning installation equipment and installation method |
| CN109848370A (en) * | 2019-04-03 | 2019-06-07 | 洛阳乾中新材料科技有限公司 | A kind of sand casting casting external form moulding tooling |
| CN110180996A (en) * | 2019-07-03 | 2019-08-30 | 陈健美 | A kind of method cracked in elimination gravitational casting |
| CN110681845A (en) * | 2019-08-28 | 2020-01-14 | 贵州航天风华精密设备有限公司 | Cabin gap pouring structure |
| CN112427608A (en) * | 2020-11-30 | 2021-03-02 | 贵州航天风华精密设备有限公司 | Large magnesium alloy special-shaped structural part casting die and process |
| CN113102690A (en) * | 2021-04-06 | 2021-07-13 | 洛阳乾中新材料科技有限公司 | Design method of casting mold |
| CN115401169A (en) * | 2022-08-30 | 2022-11-29 | 贵州安吉航空精密铸造有限责任公司 | Process method for filling large high-temperature alloy thin-wall casing support plate |
| CN118162587A (en) * | 2024-05-14 | 2024-06-11 | 贵州航天风华精密设备有限公司 | Sand casting molding device and casting method for special-shaped thin-wall castings |
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Legal Events
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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141231 |