CN106003755B - For the molding mold of carrier rocket full composite material low-temperature liquid oxygen tank and method - Google Patents
For the molding mold of carrier rocket full composite material low-temperature liquid oxygen tank and method Download PDFInfo
- Publication number
- CN106003755B CN106003755B CN201610527986.7A CN201610527986A CN106003755B CN 106003755 B CN106003755 B CN 106003755B CN 201610527986 A CN201610527986 A CN 201610527986A CN 106003755 B CN106003755 B CN 106003755B
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- China
- Prior art keywords
- composite material
- trunk section
- main shaft
- liquid oxygen
- foam
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/24—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass dies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
Abstract
The present invention provides one kind being used for the molding mold of carrier rocket full composite material low-temperature liquid oxygen tank and method, including：Front apron, main shaft, foam piece and rear baffle；The main shaft includes trunk section and the connecting pole at trunk section both ends is arranged, and the connecting pole is used to main shaft being clamped in wrapping machine；Multiple foam pieces are combined into Thysanophyllum assembly in the trunk section；The both ends of the trunk section are respectively arranged with front apron and rear baffle, and the foam piece is squeezed and is mounted in the trunk section.The mold for adding foam piece combining form in the present invention by using metal main shaft realizes lightweight, high-precision, cleaning, low cost, and can meet the Collapsible mould of the manufacture of oversize carrier rocket composite material low-temperature liquid oxygen tank.
Description
Technical field
The present invention relates to composite moldings, and in particular, to one kind being used for carrier rocket full composite material low-temperature liquid oxygen
The molding mold of tank and method.
Background technology
With the development of Space Science and Technology, the raising of spacecraft performance is increasingly paid attention to by each developed country.How
The delivery efficiency of spacecraft is improved, cost is reduced and becomes in the important research of the following space transporter and aerospace craft
Hold.Fuel tank becomes and subtracts as the following critical component for carrying out the manned deep space of Low Earth Orbit and exploring the spacecraft of task
The emphasis of weight, and the composite material with high specific strength, specific modulus becomes the Future Spacecraft tank of various countries' aerospace enterprise group concern
Important materials, and metallic tank by the complete substitute technology of composite material also by internationally recognized to be the skill of " change game rule "
Art.
It is investigated according to pertinent literature, the existing pressure vessel using carbon fiber enhancement resin base composite material as winding layer
Shaped form be mostly Wrapping formed on liner (including metal inner lining, plastic inner lining and air bag), wherein composite layer is only
As structure sheaf.
Traditional mainly has without the used mold of liner composite material product：Simple metal core model, low-melting alloy core model, punching
Wash formula core model, combination assembled core model, inflatable core model etc..Table 1 respectively compares the advantage and disadvantage of several molds.
1 detachable core die type of table and feature
| Serial number | Mould-type | Advantage | Disadvantage |
| 1 | Simple metal | Precision is high, and stability is good | Weight is big, price, and demoulding is difficult |
| 2 | Low-melting alloy | Plastic complicated shape | Prepare difficult, demoulding environmental requirement height |
| 3 | Flushing type | It is convenient in demoulding | Precision is low, and stability is poor |
| 4 | It is combination assembled | Lighter in weight, precision are good | It is longer to demould the period |
| 5 | Inflatable | It is light-weight, it is convenient in demoulding | Preparation acquires a certain degree of difficulty, and precision is relatively low |
Since the size of carrier rocket composite material low-temperature liquid oxygen tank is larger, tank overall dimensions precision has certain want
It asks, and the purity requirements of inner wall are very high, therefore lighter in weight need to be used, formed precision is high, demoulds thorough, noresidue mould
Tool form.Several die forms in Integrated comparative table 1, wherein combination assembled core model is best mold pattern.Traditional group
Assembled core model is closed to be divided into as assembled piece type composite core formwork, skeleton composite core formwork.Assembled piece type composite core formwork generally uses metal material
Matter is especially unsuitable for being wound in for the carrier rocket composite material tank of oversize due to being limited by wrapping machine weight
Type.Skeleton composite core formwork is generally divided into metallic framework or composite material skeleton, metallic framework due to weight not yet
The manufacture claim of tank can be met；And composite material skeleton does not have the production of ripe material prepreg also due to the country,
And the reasons such as external import is limited cause its application limited.
In conclusion the present invention replaces tradition by the hard foam with high rigidity Light deformation under lightweight, high temperature
Metal splits effectively alleviate the quality of mold, improve the dimensional accuracy after product hot setting, can meet oversize
The manufacture of carrier rocket composite material low-temperature liquid oxygen tank.In addition, the mold can also promote the other large sizes of aerospace without liner
Wind the manufacture of component.
Invention content
For the defects in the prior art, the object of the present invention is to provide one kind being used for carrier rocket full composite material low temperature
The molding mold of LOX tank and method, can avoid conventional ASSEMBLE mold weight is big, precision is low, product inner wall demoulding have it is residual
The technological deficiency stayed.
According to provided by the present invention for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank, packet
It includes：Front apron, main shaft, foam piece and rear baffle；
The main shaft includes trunk section and the connecting pole at trunk section both ends is arranged, and the connecting pole is used for main shaft
It is clamped on wrapping machine；
Multiple foam pieces are combined into Thysanophyllum assembly in the trunk section；The both ends of the trunk section are set respectively
It is equipped with front apron and rear baffle, the foam piece is squeezed and is mounted in the trunk section.
Preferably, front apron connects one end of one end and the Thysanophyllum of the trunk section；Rear baffle connects the master
The other end of the other end and the Thysanophyllum of dry section.
Preferably, the front apron, be both provided with the first counter sink and the second counter sink on rear baffle；First countersunk head
The position in hole is corresponding with first threaded hole at both ends of trunk section；The position of second counter sink and the Thysanophyllum
Both ends the second threaded hole it is corresponding.
Preferably, the diameter dimension of main shaft both ends connecting pole is 50-90mm, the intermediate a diameter of 0.4-4m of trunk section.
Preferably, the main shaft hollow metal structure, thickness 1-20mm.
Preferably, the foam piece is made of rigid foam；The front apron, rear baffle are made of metal.
Preferably, the quantity of the first counter sink of the front apron and the second counter sink is multiple；
Multiple first counter sinks and the second counter sink are respectively along the circumferential array of the front apron；
First counter sink of the rear baffle and the quantity of the second counter sink are multiple；
Multiple first counter sinks and the second counter sink are respectively along the circumferential array of the rear baffle.
Preferably, the foam piece uses material to be made of Polymethacrylimide (PMI) rigid foam, hard bubble
The density of foam is 71-110kg/m3, and temperature in use is not less than 180 DEG C.
Preferably, the front/rear end of the Thysanophyllum is respectively provided with embedded part, and threaded hole is processed in embedded part.
The present invention is provided to the making sides of the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank
Method includes the following steps：
Step 1：Main shaft with connection column diameter and trunk section diameter is produced using steel plate；
Step 2：Using rigid foam made of Polymethacrylimide, spelled using numerically-controlled machine tool processing polylith foam
Block, processing content mainly have Surface Milling, contour machining and drilling, and are buried after completing multiple aluminium alloy embedded parts；
Step 3：Front apron and rear baffle are processed using aluminium alloy；
Step 4：Polylith foam piece is circumferentially carried out along main shaft it is assembled formed Thysanophyllum and with front apron, rear baffle and
Thysanophyllum is spirally connected.
Compared with prior art, the present invention has following advantageous effect：
1, add the mold of foam piece combining form in the present invention by using metal main shaft, realize lightweight, high-precision,
Cleaning, low cost, and the Collapsible mould of the manufacture of oversize carrier rocket composite material low-temperature liquid oxygen tank can be met；
2, foam piece of the present invention is made of the hard foam with high rigidity Light deformation under low-density, high temperature,
It can match with composite material LOX tank solidification temperature, realize the use of mold at high temperature, be effectively guaranteed product ruler
Very little precision；
3, front apron, rear baffle and main shaft, foam piece are connected and fixed by the present invention respectively by screw, pass through the connection
Mode ensures the globality of foam piece and the close connection of foam piece and main shaft, avoids in the Wrapping formed process of tank
In Relative sliding between each structure.
Description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the structural decomposition diagram of the present invention；
Fig. 2 is the structural schematic diagram of the present invention.
In figure：
1 is baffle；
2 be main shaft foam；
3 be piece；
4 be rear baffle.
Specific implementation mode
With reference to specific embodiment, the present invention is described in detail.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
In the present embodiment, molding removable provided by the present invention for carrier rocket full composite material low-temperature liquid oxygen tank
Mold is unloaded, including：Front apron 1, main shaft 2, foam piece 3 and rear baffle 4；
The main shaft 2 includes trunk section and the connecting pole at trunk section both ends is arranged, and the connecting pole will be for that will lead
Axis 2 is clamped on wrapping machine；
Multiple foam pieces 3 are combined into Thysanophyllum assembly in the trunk section；Distinguish at the both ends of the trunk section
It is provided with front apron 1 and rear baffle 4, the foam piece 3 is squeezed and is mounted in the trunk section.
Front apron 1 connects one end of one end and the Thysanophyllum of the trunk section；Rear baffle 4 connects the trunk section
The other end of the other end and the Thysanophyllum.
It is both provided with the first counter sink and the second counter sink on the front apron 1, rear baffle 4；First counter sink
Position is corresponding with first threaded hole at both ends of trunk section；The position of second counter sink and the two of the Thysanophyllum
Second threaded hole at end is corresponding.
The diameter dimension of 2 both ends connecting pole of the main shaft is 50-90mm, the intermediate a diameter of 0.4-4m of trunk section.Specifically,
A diameter of 90mm of connecting pole, the point diameter of trunk section are 325mm, a diameter of 318mm in rear end, and the rear ends of trunk section are equal
6 M8 threaded holes of cloth, for the connection with front apron 1, rear baffle 4.
2 hollow metal structure of the main shaft, thickness 1-20mm specially use thickness for steel plate (steel rolling, the forging of 4mm
Steel) or aluminium alloy plate (2A12,2A14) be made.
The foam piece 3 is made of rigid foam；The front apron 1, rear baffle 4 are made of metal.Described
Foam piece 3 shares 18 pieces of foam composition assembly, and there are 10 embedded parts in Thysanophyllum front and rear end, M10 is equipped on each embedded part
Threaded hole.It is connect with front apron 1, rear baffle 4 by being spirally connected, is in close contact with Thysanophyllum in main shaft 2 by squeezing.
First counter sink of the front apron 1 and the quantity of the second counter sink are multiple；Multiple first counter sinks and
Second counter sink is respectively along the circumferential array of the front apron 1；The number of the first counter sink and the second counter sink of the rear baffle 4
Amount is multiple；Multiple first counter sinks and the second counter sink are respectively along the circumferential array of the rear baffle 4.
More specifically, the front apron 1, rear baffle 4, material are steel plate (hot-rolled steel, the forging that thickness is 18mm
Steel) or aluminium alloy plate (2A12,2A14), the front and rear sides of trunk section are respectively arranged on, are the round tablets of a diameter of 450mm.
Front apron 1, rear baffle 4 be equipped with two groups of counter sinks, by screw, respectively with the M8 threaded holes of main shaft 2, the M10 of foam piece 3
Threaded hole connects, and is followed successively by from inside to outside：It connect with mold main shaft 2, connect with 3 mold of foam piece, effectively exempted from tank
Relative sliding during Wrapping formed between each structure.
The foam piece 3 uses material to be made of Polymethacrylimide PMI rigid foams, the density of rigid foam
For 71-110kg/m3, temperature in use is not less than 180 DEG C.
The front/rear end of the Thysanophyllum is respectively provided with embedded part, and threaded hole is processed in embedded part.
The present invention is provided to the making sides of the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank
Method includes the following steps：
Step 1：It is produced using steel plate, there is the main shaft of connection column diameter and trunk section diameter；Specifically, using
Steel plate (hot-rolled steel) is produced after 2mm, length 1800mm, a diameter of 90mm of thin segment, a diameter of 325mm of thick section main shaft.
Step 2：Using rigid foam made of Polymethacrylimide, spelled using numerically-controlled machine tool processing polylith foam
Block, processing content mainly have Surface Milling, contour machining and drilling, and are buried after completing multiple aluminium alloy embedded parts；Specifically, adopting
The PMI rigid foams for being 110kg/m3 with density process 18 pieces of foam pieces using numerically-controlled machine tool, and processing content mainly has curved surface
Milling, contour machining and drilling, and buried after completing 10 2A12 aluminium alloy embedded parts.
Step 3：Front apron and rear baffle are processed using aluminium alloy；
Step 4：Polylith foam piece is circumferentially carried out along main shaft it is assembled formed Thysanophyllum and with front apron, rear baffle and
Thysanophyllum is spirally connected.Specifically, 18 pieces of foam pieces are carried out assembly along main shaft circumferential direction, front and rear baffle is used in combination to be carried out spiral shell
It connects.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (9)
1. one kind being used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank, which is characterized in that including：
Front apron (1), main shaft (2), foam piece (3) and rear baffle (4)；
The main shaft (2) includes trunk section and the connecting pole at trunk section both ends is arranged, and the connecting pole is used for main shaft
(2) it is clamped on wrapping machine；
Multiple foam pieces (3) are combined into Thysanophyllum assembly in the trunk section；The both ends of the trunk section are set respectively
It is equipped with front apron (1) and rear baffle (4), the foam piece (3) is squeezed and is mounted in the trunk section；
Front apron (1) connects one end of one end and the Thysanophyllum of the trunk section；Rear baffle (4) connects the trunk section
The other end of the other end and the Thysanophyllum.
2. according to claim 1 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, the front apron (1), rear baffle are both provided with the first counter sink and the second counter sink on (4)；Described first is heavy
The position of head bore is corresponding with first threaded hole at both ends of trunk section；The position of second counter sink and the foam
Second threaded hole at the both ends of column is corresponding.
3. according to claim 1 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, the diameter dimension of main shaft (2) both ends connecting pole is 50-90mm, the intermediate a diameter of 0.4-4m of trunk section.
4. according to claim 1 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, main shaft (2) the hollow metal structure, thickness 1-20mm.
5. according to claim 1 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, the foam piece (3) is made of rigid foam；The front apron (1), rear baffle (4) use made of metal
At.
6. according to claim 2 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, the first counter sink of the front apron (1) and the quantity of the second counter sink are multiple；
Multiple first counter sinks and the second counter sink are respectively along the circumferential array of the front apron (1)；
First counter sink of the rear baffle (4) and the quantity of the second counter sink are multiple；
Multiple first counter sinks and the second counter sink are respectively along the circumferential array of the rear baffle (4).
7. according to claim 2 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, the foam piece (3) uses material to be made of Polymethacrylimide (PMI) rigid foam, hard bubble
The density of foam is 71-110kg/m3, temperature in use is not less than 180 DEG C.
8. according to claim 1 be used for the molding Collapsible mould of carrier rocket full composite material low-temperature liquid oxygen tank,
It is characterized in that, the front/rear end of the Thysanophyllum is respectively provided with embedded part, threaded hole is processed in embedded part.
9. a kind of claim 1 to 8 any one of them for carrier rocket full composite material low-temperature liquid oxygen tank is molding can
The production method for dismantling mold, which is characterized in that include the following steps：
Step 1：Main shaft with connection column diameter and trunk section diameter is produced using steel plate；
Step 2：Using rigid foam made of Polymethacrylimide, polylith foam piece is processed using numerically-controlled machine tool, is added
Work content mainly has Surface Milling, contour machining and drilling, and is buried after completing multiple aluminium alloy embedded parts；
Step 3：Front apron and rear baffle are processed using aluminium alloy；
Step 4：Polylith foam piece is circumferentially carried out along main shaft assembled to form Thysanophyllum and with front apron, rear baffle and foam
Column is spirally connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610527986.7A CN106003755B (en) | 2016-07-06 | 2016-07-06 | For the molding mold of carrier rocket full composite material low-temperature liquid oxygen tank and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610527986.7A CN106003755B (en) | 2016-07-06 | 2016-07-06 | For the molding mold of carrier rocket full composite material low-temperature liquid oxygen tank and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106003755A CN106003755A (en) | 2016-10-12 |
| CN106003755B true CN106003755B (en) | 2018-07-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610527986.7A Active CN106003755B (en) | 2016-07-06 | 2016-07-06 | For the molding mold of carrier rocket full composite material low-temperature liquid oxygen tank and method |
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| CN111016223A (en) * | 2019-11-08 | 2020-04-17 | 北京宇航系统工程研究所 | Detachable combined tool for manufacturing lining-free composite material storage box |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2270633B (en) * | 1992-09-22 | 1995-08-09 | Tsai Son Kung | Method of making fiber-reinforced plastic cue having a core |
| GB9718211D0 (en) * | 1997-08-29 | 1997-11-05 | James Peter | A lighter than air low vacuum air displacement -the bucky balloon |
| JP4617411B2 (en) * | 2003-02-03 | 2011-01-26 | 国立大学法人九州大学 | High pressure tank manufacturing method and high pressure tank manufacturing apparatus |
| CN2848695Y (en) * | 2005-11-28 | 2006-12-20 | 中国船舶重工集团公司第七一五研究所 | Composite underwater machine wing unit |
| CN101314259A (en) * | 2007-05-29 | 2008-12-03 | 上海复合材料科技有限公司 | Molding method for composite material satellite joint |
| CN105437572B (en) * | 2015-12-11 | 2018-04-17 | 上海复合材料科技有限公司 | Carrier rocket full composite material low-temperature liquid oxygen tank and its manufacture method |
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