CN205414313U - Magnesium structure equipment for manufacturing is cast to large -scale spacecraft - Google Patents
Magnesium structure equipment for manufacturing is cast to large -scale spacecraft Download PDFInfo
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- CN205414313U CN205414313U CN201520956828.4U CN201520956828U CN205414313U CN 205414313 U CN205414313 U CN 205414313U CN 201520956828 U CN201520956828 U CN 201520956828U CN 205414313 U CN205414313 U CN 205414313U
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Abstract
The utility model relates to a magnesium structure equipment for manufacturing is cast to large -scale spacecraft, it includes sand box unit, psammitolite unit and casting unit, the sand box unit by plane sand box, excircle sand box, in first in circle sand box and the second circle sand box constitute, the psammitolite unit comprises basement psammitolite, interior psammitolite and top layer psammitolite, the casting unit comprises drainage sprue and runner basin. This equipment passes through effective combination of sand box unit, psammitolite unit and casting unit, effectively utilizes the combination of sand box and psammitolite and has realized that one set of sand box is simple, high -efficient, take up an area of few purpose, has solved the problem among the prior art.
Description
Technical field
This utility model relates to a kind of Large Spacecraft casting magnesium structural member manufacture equipment, is used for manufacturing spacecraft propulsion modular structure instrument disk, belongs to casting technology field.
Background technology
Since entering 21st century, the spacecraft overall dimensions such as the aerospace industry of China obtains significant progress, satellite are gradually increased, and require platform structure lightweight.In structural metallic materials, the minimum magnesium alloy of density with its good bio-compatibility, the highest specific stiffness and specific strength, excellent processing performance, preferable decay resistance in spacecraft macrotype platform widely used.
Along with developing rapidly of China's aerospace industry, go into seriously the carrying out of detection, the foundation of space station, the demand of Future Launch Rocket, large and close mode development to spacecraft cast product are had higher requirement, the overall dimensions of heavy castings product is up to 4000mm, and the cast structure part that secondary military repeater satellite, low rail remote sensing, high rail electronic reconnaissance large platform satellite, cargo ship etc. use then is up to
At present, the ultra-large type magnesium alloy structural part technology of China below 2000mm is the most ripe, but reaches for sizeEspeciallyAbove ultra-large type magnesium alloy component is also anxious to be developed.In prior art, when casting above ultra-large type magnesium alloy component, remain in and use in traditional Fixture Design method, cast the upper drag box of same oversize the most respectively, and on completing, after the casting of drag box, also need to carry out the casting of integral sand core.
Owing to the upper drag box floor space of ultra-large type magnesium alloy component is very big, so requiring the highest for production site, storage space, this technology is not suitable for small-sized production unit；On the other hand, the component casting of upper drag box is too big because of size, so also improving the difficulty of production, time-consumingly increasing, reduces production efficiency.
Utility model content
Technical problem to be solved in the utility model be in prior art for spacecraft casting magnesium structural member manufacture be required for using upper drag box structure fabrication, the problem that floor space is big, production difficulty is big, and then provide one to save occupation of land, technology Combined type sand box system simple, easy-operating.
For solving above-mentioned technical problem, this utility model is achieved through the following technical solutions:
A kind of Large Spacecraft casting magnesium structural member manufacture equipment, comprising:
Sandbox unit, core unit and casting unit；
Sandbox unit includes:
Plane sandbox, has circular sandbox support, and support includes the first annulus that annular is nested, and concentric with the first annulus and be positioned at the second annulus within described first annulus；It is provided with multiple equally distributed, for connecting the radially connected part of two annulus between the first annulus and the second annulus；Described plane sandbox is made up of the plane sub-sand case of several deciles；
Cylindrical sandbox, for annular stent, the internal diameter of described cylindrical sandbox is equal to the internal diameter of plane sandbox the first annulus；
First inner circle sandbox, for annular stent；In being arranged on the second annulus of described plane sandbox and it is arranged concentrically with the second annulus；
Second inner circle sandbox, for annular stent, the internal diameter of described second inner circle sandbox is more than the internal diameter of the first inner circle sandbox, and the first inner circle sandbox and the second inner circle sandbox are concentrically nested；Described second inner circle sandbox is equal with the second internal radius of plane sandbox；
Core unit includes:
Substrate core, described substrate core is made up of the splicing of some substrate sub-sand cores；
Interior core, is arranged on the top layer of substrate core, contacts setting with substrate core；
Top layer core, is arranged on the top layer of interior core, contacts setting with interior core；
Described substrate core, interior core with top layer core all in circular and shape, size identical；
Top layer core is made up of the splicing of several top layers sub-sand cores, and described top layer sub-sand core is sector structure, offers multiple through hole on the sub-sand core of each fan-shaped top layer, in multiple through holes at least one be the first sprue, at least two through holes are rising head；
Interior core offers, in the position corresponding with described top layer core sprue, the second sprue connected with the first sprue；Interior core is made up of sub-sand core splicing in several, and form the foundry goods die cavity that longitudinal section is I-shaped, described foundry goods die cavity connects with rising head, connect with described foundry goods die cavity and offering ingate near described second sprue, connect further with described ingate and offer cross gate further towards described second sprue；Interior sub-sand core, after splicing, forms the foundry goods die cavity of annular I-shaped, annular ingate, circular cross-runner；
Substrate core offers cast gate whirlpool, the connection corresponding with described second sprue of described cast gate whirlpool is arranged, connecting with cast gate whirlpool extended has bottom cross gate, and described bottom cross gate is correspondingly arranged at below cross gate described in interior core and is connected by cast gate whirlpool with described cross gate；Substrate sub-sand core, after splicing, forms annular bottom cross gate；
Described substrate core, interior core and top layer core may be contained between described plane core the first annulus inner edge and described second inner circle sandbox outer rim；
Casting unit includes:
Drain sprue, connects with described first sprue, and the cross section of described drain sprue is L-shaped；
Pouring basin, described pouring basin arranges the top of described drain sprue and is connected with drain sprue.
Each connector offers socket, the annular stent of cylindrical sandbox is evenly distributed with multiple insertable plug-in unit adaptive with described socket；Second annulus is provided with the projection towards the first annulus.
On described plane sandbox, being additionally provided with the 3rd annulus, described 3rd annulus is arranged between described first annulus and the second annulus, through described 3rd annulus of each described connector.
Each described top layer sub-sand core is made up of at least three top layer sub-sand core micro unit, and described top layer sub-sand core micro unit radially divides equally described top layer sub-sand core.
On the radial section of top layer core, it is provided with first sprue and two through holes, and the first sprue is positioned at the centre position of said two through hole.
Each interior sub-sand core is made up of some interior sub-sand core micro units, described interior sub-sand core micro unit is along substrate sub-sand core diameter to being made up of three sector element splicings the most respectively, and middle sector element is made up of the peripheral cell of remaining area of the circular micro unit and this sector element of mean allocation that are positioned at center.
Described second sprue is positioned at the center of circular micro unit.
Each described substrate sub-sand core is made up of some substrate sub-sand core micro units, described substrate sub-sand core micro unit along substrate sub-sand core diameter to being made up of the splicing of three sector elements the most respectively, middle sector element is made up of the peripheral cell of remaining area of the circular micro unit and this sector element of mean allocation that are positioned at center, and bottom cross gate is arranged on described circular micro unit.
First sprue and the second sprue are cylindrical；Rising head is trapezoidal, and rising head upper end width is more than lower end width.
Technique scheme of the present utility model has the advantage that compared to existing technology
Large Spacecraft described in the utility model casting magnesium structural member manufacture equipment, it includes sandbox unit, core unit and casting unit, wherein, sandbox unit includes plane sandbox, there is circular sandbox support, support includes the first annulus that annular is nested, and concentric with the first annulus and be positioned at the second annulus within described first annulus；It is provided with multiple equally distributed, for connecting the radially connected part of two annulus between the first annulus and the second annulus；Described plane sandbox is made up of the plane sub-sand case of several deciles；Cylindrical sandbox, for annular stent, the internal diameter of described cylindrical sandbox is equal to the internal diameter of plane sandbox the first annulus；First inner circle sandbox, for annular stent；In being arranged on the second annulus of described plane sandbox and it is arranged concentrically with the second annulus；Second inner circle sandbox, for annular stent, the internal diameter of described second inner circle sandbox is more than the internal diameter of the first inner circle sandbox, and the first inner circle sandbox and the second inner circle sandbox are concentrically nested；Described second inner circle sandbox is equal with the second internal radius of plane sandbox.This structure is by unique plane sandbox, cylindrical sandbox, the modular design of inner circle sandbox, solve the technological difficulties needing to arrange drag box in prior art, such that it is able to utilize a set of sandbox to solve the casting problem of Large Spacecraft, significantly save floor space, reduced production difficulty.
Core unit achieves combined type sand core structure, and this combined type sand core includes three layers of sand core structure, respectively substrate core, interior core and top layer core；And interior core is arranged on the top layer of substrate core, contact setting with substrate core；Top layer core is arranged on the top layer of interior core, contacts setting with interior core；Substrate core, interior core with top layer core all in circular and shape, size identical.Top layer core is made up of the splicing of several sector structure top layers sub-sand cores, offers multiple through hole on the sub-sand core of each fan-shaped top layer, in multiple through holes at least one be the first sprue, at least two through holes are rising head；Interior core offers the second sprue connected with the first sprue in the position corresponding with top layer core sprue；Interior core is made up of sub-sand core splicing in several, and form the foundry goods die cavity that longitudinal section is I-shaped, described foundry goods die cavity connects with rising head, connect with described foundry goods die cavity and offering ingate near described second sprue, connect further with ingate and offer cross gate further towards the second sprue；Interior sub-sand core, after splicing, forms the foundry goods die cavity of annular I-shaped, annular ingate, circular cross-runner.Substrate core is made up of the splicing of some substrate sub-sand cores equally.
This combined type sand core have employed separate combination type sand core structure first, i.e. substrate core, interior core and top layer core is the sand core structure of concatenation module, on the one hand ensure that casting liquid can pass through top layer core, the structure design forming circulation of interior core, unique pouring channel structure, ensure that the circulation smoothly of casting liquid, casting, also eliminate in prior art the problem that the floor space using the upper drag box of entirety and the sand core structure up and down of correspondence to be brought is big, technical difficulty big, the most, production efficiency is low simultaneously.And when non-fabrication state, combined type sand core can also be deposited in superposition, is greatly saved floor space.
Large Spacecraft structural member manufacture equipment described in the utility model, by sandbox unit, core unit and effective combination of casting unit, effectively utilize sandbox and core combination achieve a set of sandbox simple, efficiently, take up an area few purpose, solve the problems of the prior art.
Accompanying drawing explanation
In order to make content of the present utility model be more likely to be clearly understood, below according to specific embodiment of the utility model and combine accompanying drawing, this utility model is described in further detail, wherein
Fig. 1 is plane sandbox structural representation；
Fig. 2 is cylindrical sandbox structural representation；
Fig. 3 is the first inner circle sandbox and the second inner circle sandbox structural representation；
Fig. 4 is top layer sand core structure schematic diagram；
Fig. 5 is interior sand core structure schematic diagram；
Fig. 6 is substrate sand core structure schematic diagram；
Fig. 7 is equipment assembled state longitudinal sectional view.
In figure, reference is expressed as: 1-plane sandbox, 2-cylindrical sandbox, 3-the first inner circle sandbox, 4-the second inner circle sandbox, 5-the first annulus, 6-the second annulus, 7-connector, 8-plane sub-sand case, 9-the 3rd annulus, 10-pouring basin, 100-drain sprue, 11-top layer core, core in 12-, 13-substrate core, 14-top layer sub-sand core, 15-the first sprue, 16-rising head, 17-the second sprue, sub-sand core 19-foundry goods type in 18-, 110-ingate, 111-cross gate, 112-bottom cross gate, 113-substrate sub-sand core, 114-top layer sub-sand core micro unit, sub-sand core micro unit in 115-, 116-circle micro unit, 117-peripheral cell, 118-cast gate whirlpool.
Detailed description of the invention
Large Spacecraft described in the utility model casting magnesium structural member manufacture equipment, it includes sandbox unit, core unit and casting unit.
Sandbox unit includes plane sandbox 1, cylindrical sandbox the 2, first inner circle sandbox 3 and the second inner circle sandbox 4 being positioned at bottom.
Plane sandbox 1, as shown in Figure 1, has circular sandbox support, and support includes the first annulus 5 that annular is nested, and concentric with the first annulus 5 and be positioned at the second annulus 6 within described first annulus 5；It is provided with multiple equally distributed, for connecting the radially connected part 7 of two annulus between the first annulus 5 and the second annulus 6；As preferred embodiment, preferred planar sandbox 1 is made up of the plane sub-sand case 8 of several deciles, is most preferably made up of the plane sub-sand case 8 of 8 deciles；
Cylindrical sandbox 2, as shown in Figure 2, for annular stent, the internal diameter of cylindrical sandbox 2 is equal to the internal diameter of plane sandbox 1 first annulus 5；
First inner circle sandbox 3, as shown in Figure 3, for annular stent；In being arranged on the second annulus 6 of described plane sandbox 1 and it is arranged concentrically with the second annulus 6；
Second inner circle sandbox 4, the most as shown in Figure 3, for annular stent, the internal diameter of the second inner circle sandbox 4 is more than the internal diameter of the first inner circle sandbox 3, and the first inner circle sandbox 3 is concentrically nested with the second inner circle sandbox 4；Described second inner circle sandbox 4 is equal with the second annulus 6 internal diameter of plane sandbox 1.
Each connector 7 offers socket, the annular stent of cylindrical sandbox 2 is evenly distributed with multiple insertable plug-in unit adaptive with described socket；Second annulus 6 is provided with the projection towards the first annulus 5.
On described plane sandbox 1, being additionally provided with the 3rd annulus 9, described 3rd annulus 9 is arranged between described first annulus 5 and the second annulus 6, through described 3rd annulus 9 of each described connector 7.
Large Spacecraft manufacture sandbox system equipment described in the utility model also includes that core unit, core unit include substrate core 13, interior core 12 and top layer core 11；When assembling, substrate core 13, interior core 12 and top layer core 11 may be contained between described plane sandbox 1 first annulus 5 inner edge and described second inner circle sandbox 4 outer rim.
Wherein, as shown in Figure 4, it includes being arranged on the top layer of interior core 12 top layer core 11 structure, contacts setting with interior core 12.From in shape, it is annular.Top layer core 11 is made up of several top layer sub-sand core 14 splicings, described top layer sub-sand core 14 is in sector structure, each fan-shaped top layer sub-sand core 14 offers multiple through hole, in multiple through holes at least one be the first sprue 15, at least two through holes are rising head 16.Wherein, setting for top layer sub-sand core 14, its quantity can be set according to Practical Project demand, thus the size of each top layer sub-sand core 14 is determined according to quantity, additionally, the actual demand of the design engineering to be considered for through hole, but no matter the number of through hole arranges how many, in through hole to be ensured, one is the first sprue 15, and two is rising head 16.For sprue and the setting of rising head 16, general first sprue 15 to be arranged on the position between two rising heads 16, as preferred embodiment, the position of the first sprue 15 and two rising heads 16 can be designed according to following setting: i.e. on the radial section of top layer core 11, first sprue 15 is positioned at the centre position of said two through hole, it is to say, two rising heads 16 are symmetrical arranged centered by the first sprue 15.
As shown in Figure 5, it is arranged on the top layer of substrate core 13 structure of interior core 12, contacts setting with substrate core 13.From in shape, interior core 12 is same in annular, identical with the shape of aforementioned top layer core 11, size.From the point of view of structure, interior core 12 offers the second sprue 17 connected with the first sprue 15 in the position corresponding with described top layer core 11 sprue；Interior core 12 is made up of sub-sand core 18 splicing in several, and it is internally formed, at interior core 12, the foundry goods die cavity 19 that longitudinal section is I-shaped, when arranging, require that foundry goods die cavity 19 connects with rising head 16, ingate 110 is offered in the direction near the second sprue 17 additionally, connect with foundry goods die cavity 19.Connect further with ingate 110 and direction further towards the second sprue 17 offers cross gate 111.The interior sub-sand core 18 of said structure, after splicing, forms the foundry goods die cavity 19 of annular I-shaped, annular ingate 110, circular cross-runner 111.
As shown in Figure 6, substrate core 13 is positioned at the lowermost end of combination core to substrate core 13 structure, and substrate core 13 is made up of the splicing of some substrate sub-sand cores 113.Substrate core 13 and interior core 12 and top layer core 11 all in circular and shape, size identical.Substrate core 13 offers cast gate whirlpool 118, cast gate whirlpool 118 connection corresponding with the second sprue 17 is arranged, connecting with cast gate whirlpool 118 extended has bottom cross gate 112, and bottom cross gate 112 is correspondingly arranged at below cross gate 111 described in interior core and is connected by cast gate whirlpool 118 with cross gate 111；Substrate sub-sand core 113, after splicing, forms annular bottom cross gate.As can preferred embodiment, combined type sand core, each top layer sub-sand core 14 be made up of at least three top layer sub-sand core micro unit 114, and described top layer sub-sand core micro unit 114 radially divides equally described top layer sub-sand core 14.Being presented in Fig. 1 the embodiment of optimum, the most each top layer sub-sand core 14 is made up of three top layer sub-sand core micro units 114 the most from inside to outside.
As preferred embodiment, combined type sand core, each interior sub-sand core 18 is made up of some interior sub-sand core micro units 115, and the quantity for interior sub-sand core micro unit 115 can be configured according to enforcement demand.The most described substrate sub-sand core 113 micro unit is made up of three sector element splicings the most respectively along substrate sub-sand core 113, and middle sector element is made up of the peripheral cell 117 of remaining area of the circular micro unit 116 and this sector element of mean allocation that are positioned at center.As the embodiment that can convert, the most described second sprue 17 is positioned at the center of circular micro unit 116.
As on the basis of above-mentioned embodiment, the most each described substrate sub-sand 113 is made up of some substrate sub-sand core 113 micro units, and the quantity for substrate sub-sand core 113 micro unit can be configured according to enforcement demand.Preferred substrate sub-sand core 113 micro unit is made up of three sector element splicings the most respectively along substrate sub-sand core 113, middle sector element is made up of the peripheral cell 117 of remaining area of the circular micro unit 116 and this sector element of mean allocation that are positioned at center, and bottom cross gate 112 is arranged in described circular micro unit 116.
In the above-described embodiments, the first sprue 15 is set and the second sprue 17 is cylinder；Rising head 16 is trapezoidal, and rising head 16 upper end width is more than lower end width.
Manufacture equipment described in the utility model also includes unit of casting, and this unit includes pouring basin 10 and drain sprue 100, and wherein, drain sprue 100 connects with the first sprue 15, and the cross section of described drain sprue 100 is L-shaped；Pouring basin 10 then arranges the top of described drain sprue 100 and is connected with drain sprue 100.
Sandbox system described in the utility model, operationally, need first the plane sub-sand case 8 of several deciles to be spliced conglobate plane sandbox 1, cylindrical sandbox 2 is positioned over the top of plane sandbox 1 again, make the overlapping placement of the first annulus 5 of cylindrical sandbox 2 peace facing sand case 1, in order to improve its stability, fixing soil property can be used to be fixed or use, and the cooperation of socket and plug-in unit is fixing is aided with fixing soil property simultaneously and fixes；Then the first inner circle sandbox 3 is positioned over the second annulus 6 inside of plane sandbox 1 and is arranged concentrically with the second annulus 6, place overlapping for the second annulus 6 of the second inner circle sandbox 4 peace facing sand case 1 simultaneously, by fixing soil property, the first inner circle sandbox 3 and the second inner circle sandbox 4 are fixed equally；Finally substrate core 13, interior core 12 and top layer core 11 being layed in successively between plane sandbox 1 first annulus 5 inner edge and described second inner circle sandbox 4 outer rim, the combination completing sandbox is arranged.Finally drain sprue 100 is arranged on above the core of top layer, and corresponding for the intersection point of the L-shaped of drain sprue 100 first sprue 15 is placed, fix by fixing soil property, pouring basin 10 is placed on the top of drain sprue 100 the most again, again fix by fixing soil property, complete the assembling of manufacture equipment.
Afterwards, casting liquid is poured into from pouring basin 10, in pouring basin 10 flow to drain sprue 100, and flow in drain sprue 100 and flow downwardly into top layer core 11 layers, casting liquid flows into through the first sprue 15 cast gate of top layer core 11, flowing to bottom cross gate 112, casting liquid is constantly accumulated liquid level in bottom cross gate 112 and is risen and then enter in cross gate 111, and the casting realizing foundry goods after being gradually full of by cross gate 111 in cross gate 111 enters die cavity produces.In casting cycle, gas, impurity and unnecessary solution will be shoved further up and be overflowed by rising head, and solution cooling volume reduces therewith, and rising head layer solution is just used for supplementing full foundry goods die cavity.
Although this utility model has passed through above-mentioned specific embodiment, it is elaborated; but; those skilled in the art should be understood that; the any form without departing from claims made on this basis and the change of details, belong to this utility model scope of the claimed.
Claims (9)
1. a Large Spacecraft casting magnesium structural member manufacture equipment, it is characterised in that including: sandbox unit, core unit and casting unit；
Sandbox unit includes:
Plane sandbox, has circular sandbox support, and support includes the first annulus that annular is nested, and concentric with the first annulus and be positioned at the second annulus within described first annulus；It is provided with multiple equally distributed, for connecting the radially connected part of two annulus between the first annulus and the second annulus；Described plane sandbox is made up of the plane sub-sand case of several deciles；
Cylindrical sandbox, for annular stent, the internal diameter of described cylindrical sandbox is equal to the internal diameter of plane sandbox the first annulus；
First inner circle sandbox, for annular stent；In being arranged on the second annulus of described plane sandbox and it is arranged concentrically with the second annulus；
Second inner circle sandbox, for annular stent, the internal diameter of described second inner circle sandbox is more than the internal diameter of the first inner circle sandbox, and the first inner circle sandbox and the second inner circle sandbox are concentrically nested；Described second inner circle sandbox is equal with the second internal radius of plane sandbox；
Core unit includes:
Substrate core, described substrate core is made up of the splicing of some substrate sub-sand cores；
Interior core, is arranged on the top layer of substrate core, contacts setting with substrate core；
Top layer core, is arranged on the top layer of interior core, contacts setting with interior core；
Described substrate core, interior core with top layer core all in circular and shape, size identical；
Top layer core is made up of the splicing of several top layers sub-sand cores, and described top layer sub-sand core is sector structure, offers multiple through hole on the sub-sand core of each fan-shaped top layer, in multiple through holes at least one be the first sprue, at least two through holes are rising head；
Interior core offers, in the position corresponding with described top layer core sprue, the second sprue connected with the first sprue；Interior core is made up of sub-sand core splicing in several, and form the foundry goods die cavity that longitudinal section is I-shaped, described foundry goods die cavity connects with rising head, connect with described foundry goods die cavity and offering ingate near described second sprue, connect further with described ingate and offer cross gate further towards described second sprue；Interior sub-sand core, after splicing, forms the foundry goods die cavity of annular I-shaped, annular ingate, circular cross-runner；
Substrate core offers cast gate whirlpool, the connection corresponding with described second sprue of described cast gate whirlpool is arranged, connecting with cast gate whirlpool extended has bottom cross gate, and described bottom cross gate is correspondingly arranged at below cross gate described in interior core and is connected by cast gate whirlpool with described cross gate；Substrate sub-sand core, after splicing, forms annular bottom cross gate；Described substrate core, interior core and top layer core may be contained between described plane core the first annulus inner edge and described second inner circle sandbox outer rim；
Casting unit includes:
Drain sprue, connects with described first sprue, and the cross section of described drain sprue is L-shaped；
Pouring basin, described pouring basin arranges the top of described drain sprue and is connected with drain sprue.
Manufacture equipment the most according to claim 1, it is characterised in that offer socket on each connector, is evenly distributed with multiple insertable plug-in unit adaptive with described socket on the annular stent of cylindrical sandbox；Second annulus is provided with the projection towards the first annulus.
Manufacture equipment the most according to claim 1 and 2, it is characterised in that on described plane sandbox, is additionally provided with the 3rd annulus, and described 3rd annulus is arranged between described first annulus and the second annulus, through described 3rd annulus of each described connector.
Manufacture equipment the most according to claim 3, it is characterised in that each described top layer sub-sand core is made up of at least three top layer sub-sand core micro unit, described top layer sub-sand core micro unit radially divides equally described top layer sub-sand core.
Manufacture equipment the most according to claim 4, it is characterised in that on the radial section of top layer core, is provided with first sprue and two through holes, and the first sprue is positioned at the centre position of said two through hole.
Manufacture equipment the most according to claim 5, it is characterized in that, each interior sub-sand core is made up of some interior sub-sand core micro units, described interior sub-sand core micro unit is along substrate sub-sand core diameter to being made up of three sector element splicings the most respectively, and middle sector element is made up of the peripheral cell of remaining area of the circular micro unit and this sector element of mean allocation that are positioned at center.
Manufacture equipment the most according to claim 4, it is characterised in that described second sprue is positioned at the center of circular micro unit.
Manufacture equipment the most according to claim 4, it is characterized in that, each described substrate sub-sand core is made up of some substrate sub-sand core micro units, described substrate sub-sand core micro unit along substrate sub-sand core diameter to being made up of the splicing of three sector elements the most respectively, middle sector element is made up of the peripheral cell of remaining area of the circular micro unit and this sector element of mean allocation that are positioned at center, and bottom cross gate is arranged on described circular micro unit.
Manufacture equipment the most according to claim 4, it is characterised in that the first sprue and the second sprue are cylindrical；Rising head is trapezoidal, and rising head upper end width is more than lower end width.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520956828.4U CN205414313U (en) | 2015-11-26 | 2015-11-26 | Magnesium structure equipment for manufacturing is cast to large -scale spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520956828.4U CN205414313U (en) | 2015-11-26 | 2015-11-26 | Magnesium structure equipment for manufacturing is cast to large -scale spacecraft |
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| CN205414313U true CN205414313U (en) | 2016-08-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520956828.4U Withdrawn - After Issue CN205414313U (en) | 2015-11-26 | 2015-11-26 | Magnesium structure equipment for manufacturing is cast to large -scale spacecraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105268915A (en) * | 2015-11-26 | 2016-01-27 | 山西神舟航天科技有限公司 | Equipment for manufacturing magnesium casting structural component of large spacecraft |
| CN107008863A (en) * | 2017-03-10 | 2017-08-04 | 共享铸钢有限公司 | The superposing type casting method of large scale annular steel-casting |
-
2015
- 2015-11-26 CN CN201520956828.4U patent/CN205414313U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105268915A (en) * | 2015-11-26 | 2016-01-27 | 山西神舟航天科技有限公司 | Equipment for manufacturing magnesium casting structural component of large spacecraft |
| CN105268915B (en) * | 2015-11-26 | 2017-09-29 | 山西神舟航天科技有限公司 | A kind of Large Spacecraft casts magnesium structural member manufacture equipment |
| CN107008863A (en) * | 2017-03-10 | 2017-08-04 | 共享铸钢有限公司 | The superposing type casting method of large scale annular steel-casting |
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