CN100494758C - Preparation metho of heat preservation and insulation soft cover used in space docking mechanism - Google Patents
Preparation metho of heat preservation and insulation soft cover used in space docking mechanism Download PDFInfo
- Publication number
- CN100494758C CN100494758C CNB2007100677106A CN200710067710A CN100494758C CN 100494758 C CN100494758 C CN 100494758C CN B2007100677106 A CNB2007100677106 A CN B2007100677106A CN 200710067710 A CN200710067710 A CN 200710067710A CN 100494758 C CN100494758 C CN 100494758C
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- Prior art keywords
- main body
- heat insulation
- soft cover
- insulation
- fabric
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- Expired - Fee Related
Links
- 238000009413 insulation Methods 0.000 title claims abstract description 37
- 238000004321 preservation Methods 0.000 title claims abstract description 18
- 230000007246 mechanism Effects 0.000 title claims abstract description 17
- 238000002360 preparation method Methods 0.000 title claims description 12
- 238000003032 molecular docking Methods 0.000 title abstract description 6
- 239000000463 material Substances 0.000 claims abstract description 53
- 239000012774 insulation material Substances 0.000 claims abstract description 31
- 230000005855 radiation Effects 0.000 claims abstract description 26
- 239000004744 fabric Substances 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 12
- 239000011248 coating agent Substances 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims abstract description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 229920004933 Terylene® Polymers 0.000 claims description 4
- 239000004411 aluminium Substances 0.000 claims description 4
- 238000005538 encapsulation Methods 0.000 claims description 4
- 238000007747 plating Methods 0.000 claims description 4
- 239000005020 polyethylene terephthalate Substances 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 4
- 229920002994 synthetic fiber Polymers 0.000 claims description 4
- 239000012209 synthetic fiber Substances 0.000 claims description 4
- 229920000297 Rayon Polymers 0.000 claims description 3
- 239000005030 aluminium foil Substances 0.000 claims description 2
- 239000002994 raw material Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 230000015572 biosynthetic process Effects 0.000 description 4
- 210000001503 joint Anatomy 0.000 description 4
- 239000000835 fiber Substances 0.000 description 3
- 239000011888 foil Substances 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
Abstract
The present invention relates to a heat preservation and insulation soft cover used by space docking mechanism and a manufacturing method thereof. The said soft cover includes main body heat insulation material and fabric coating on the inner and outer surfaces of the main body heat insulation material. The main body heat insulation material is formed by superposing several layers of low temperature heat insulation materials and radiation protection material. The said method includes following steps: (1) superposing a layer of low temperature heat insulation material with another layer of low temperature heat insulation material to form a combination, then piling multiple combinations together to form the main body heat insulation material; (2) coating the inner and outer surfaces of the main body heat insulation material with the fabric to form a fixing shape. The present invention has perfect heat insulation effect, good plasticity and light weight in order to ensure the realization of soft docking.
Description
(1) technical field
The present invention relates to a kind of space articulation mechanism with heat preservation and insulation soft cover and preparation method thereof.
(2) background technique
The outside of the earth space is owing to have the characteristic of vacuum and low temperature, handles so need carry out heat insulation, radiation proof to the equipment that is transmitted into the outer space, with the instrument of effective protection device interior, the proper functioning and the actual life of instrument.And, need all parts of docking mechanism to carry out heat-insulation and heat-preservation and radiation proof processing for the effective butt joint between two aircraft in implementation space, need the docking mechanism outer surface is covered heat insulation soft cover for this reason.Motion when heat insulation soft cover also requires to realize along with butt joint and keep certain pliability, tightness and enough intensity.
(3) summary of the invention
Technical problem to be solved by this invention is to provide a kind of can carry out heat-insulation and heat-preservation and radiation proof processing to docking mechanism, keeps the space articulation mechanism heat preservation and insulation soft cover of certain pliability, tightness and intensity simultaneously again.
Technical problem to be solved by this invention also is to provide the preparation method of a kind of above-mentioned space articulation mechanism with heat preservation and insulation soft cover.
Described space articulation mechanism heat preservation and insulation soft cover comprises the main body thermal-protective material and is coated on the fabric on the inside and outside surface of main body thermal-protective material that described main body thermal-protective material is formed by stacking by several layers Cryo Heat Insulation material and radiation proof material.
The low temperature that main body thermal-protective material of the present invention (comprising Cryo Heat Insulation material and radiation proof material) is mainly used under the vacuum is heat insulation, and fabric except that can be used for low temperature heat insulation, also as the framework of whole soft cover, improved the intensity of soft cover.Above-mentioned Cryo Heat Insulation material, radiation proof material, fabric all can adopt material commonly known in the art.
Further, described Cryo Heat Insulation material and radiation proof material are superimposed at interval.
Further, described Cryo Heat Insulation material and radiation proof material have 20～50 layers respectively.
Further, described Cryo Heat Insulation material quantitatively is 5～14g/m for being raw material with the chemical synthetic fiber
2, thickness is at the low-temperature thermal insulation paper of 0.04～0.09mm.
Further, described low-temperature thermal insulation paper adopts dry forming to be shaped.Though the low-temperature thermal insulation paper that obtains through wet papermaking also can reach this patent requirement, the low-temperature thermal insulation paper that obtains through dry forming has better intensity, more can reach this patent requirement.
Further, described chemical synthetic fiber is a viscose.
Further, the described fabric that is coated on main body thermal-protective material outer surface has seal coating.
Further, described radiation proof material is that thickness is aluminium foil or the aluminium plating terylene film of 2.0～10.0 μ m.
Space articulation of the present invention mechanism is with the preparation method of heat preservation and insulation soft cover, comprise the steps: that (1) is overlapped into a combination with one deck Cryo Heat Insulation material and one deck Cryo Heat Insulation material earlier, a plurality of combinations are superimposed form the main body thermal-protective material then;
(2) the inside and outside surface with the main body thermal-protective material coats fabric, and is fixed-type.
Further, the described fabric that is coated on main body thermal-protective material outer surface is spliced by the polylith fabric, and seam crossing is through encapsulation process.
Heat preservation and insulation soft cover of the present invention can adopt one or more Cryo Heat Insulation material, radiation proof material to be spliced according to concrete condition, considers the sealing of soft cover requirement when being spliced, and needs the butt joint place to carry out encapsulation process usually.
The present invention for realizing and being connected of miscellaneous part, need punch at the certain position of soft cover in use usually.Particularly, position at first on request during punching, go out the aperture of certain diameter again with instrument, and then seal and enhancement process around the hole with low temperature glue.
Beneficial effect of the present invention is:
(1) effect of heat insulation is good.The present invention has carried out MULTILAYER COMPOSITE with Cryo Heat Insulation material and radiation proof material, thereby the conduction of trap heat and radiation effectively makes the effect of heat insulation of soft cover reach usage requirement.
(2) have good ductility and very light deadweight to guarantee to realize soft-dock.Owing to adopted Cryo Heat Insulation material paper shape, ultra-thin and radiation proof material, make whole soft cover have good softness, reduced the deadweight of soft cover simultaneously.
(3) has the impact to soft cover when guaranteeing butt joint of enough intensity.Owing to coat with yarn fabric, make the intensity of whole soft cover reach the requirement of process stipulation on the inside and outside surface of main body thermal-protective material.
(4) has good air tightness.Because outermost surface clad material (fabric) passed through the coating processing, and stick with glue agent at seam crossing and carry out encapsulation process, make whole soft cover have the good air-tightness energy.
(5) profiling is good.The present invention adopts the Cryo Heat Insulation material of paper shape, thickness only is (0.04～0.09) mm, and the thickness of compound with it radiation proof material also only is (2.0～10.0) μ m, has good ductility and certain tension stress, can produce multiple difform soft cover.
(6) good stability.The venting rate of the present invention under vacuum is very little, and all materials of selecting for use all have for a long time in various weather conditionss, good stable, thereby guarantees the long-term, stable of insulation effect.
(4) embodiment
The invention will be further described below in conjunction with embodiment, but protection scope of the present invention is not limited to this.
The preparation of heat preservation and insulation soft cover of embodiment 1 space articulation mechanism
(1) earlier one deck Cryo Heat Insulation material and one deck radiation proof material are overlapped into a combination, a plurality of combinations are superimposed form the main body thermal-protective material then;
(2) the inside and outside surface with the main body thermal-protective material coats fabric, and is fixed-type.Described Cryo Heat Insulation material selection quantitatively is 7g/m
2, thickness is 0.07mm, be the low-temperature thermal insulation paper that material of main part adopts the dry forming formation technique to produce with the viscose.
Described radiation proof material is selected the aluminium plating terylene film of 3.8 μ m for use.
The preparation of heat preservation and insulation soft cover of embodiment 2 space articulation mechanisms
(1) earlier one deck Cryo Heat Insulation material and one deck radiation proof material are overlapped into a combination, a plurality of combinations are superimposed form the main body thermal-protective material then;
(2) the inside and outside surface with the main body thermal-protective material coats fabric, and is fixed-type.
Described Cryo Heat Insulation material selection quantitatively is 7g/m
2, thickness is 0.05mm, be the low-temperature thermal insulation paper that material of main part adopts the dry forming formation technique to produce with the polyster fibre.
Described radiation proof material is selected the aluminium plating terylene film of 3.8 μ m for use.
The preparation of heat preservation and insulation soft cover of embodiment 3 space articulation mechanisms
(1) earlier one deck Cryo Heat Insulation material and one deck radiation proof material are overlapped into a combination, a plurality of combinations are superimposed form the main body thermal-protective material then;
(2) the inside and outside surface with the main body thermal-protective material coats fabric, and is fixed-type.
Described Cryo Heat Insulation material selection quantitatively is 10g/m
2, thickness is 0.09mm, be the low-temperature thermal insulation paper that material of main part adopts the dry forming formation technique to produce with the polyster fibre.
Described radiation proof material is selected the aluminum foil film of 8 μ m for use.
The preparation of heat preservation and insulation soft cover of embodiment 4 space articulation mechanisms
(1) earlier one deck Cryo Heat Insulation material and one deck radiation proof material are overlapped into a combination, a plurality of combinations are superimposed form the main body thermal-protective material then;
(2) the inside and outside surface with the main body thermal-protective material coats fabric, and is fixed-type.
Described Cryo Heat Insulation material selection quantitatively is 12g/m
2, thickness is 0.05mm, be the low-temperature thermal insulation paper that material of main part adopts the dry forming formation technique to produce with the polyster fibre.
Described radiation proof material is selected the aluminum foil film of 5 μ m for use.
Claims (2)
1, a kind of space articulation mechanism is with the preparation method of heat preservation and insulation soft cover, it is characterized in that: described heat preservation and insulation soft cover comprises the main body thermal-protective material and is coated on the fabric on the inside and outside surface of main body thermal-protective material that described main body thermal-protective material is formed by stacking by several layers Cryo Heat Insulation material and radiation proof material; Described Cryo Heat Insulation material quantitatively is 5～14g/m for being raw material with the chemical synthetic fiber
2, thickness is at the low-temperature thermal insulation paper of 0.04～0.09mm; Described low-temperature thermal insulation paper adopts dry forming to be shaped; Described chemical synthetic fiber is a viscose;
The described fabric that is coated on main body thermal-protective material outer surface has seal coating;
Described radiation proof material is that thickness is aluminium foil or the aluminium plating terylene film of 2.0～10.0 μ m;
Described preparation method comprises the steps:
(1) earlier one deck Cryo Heat Insulation material and one deck radiation proof material are overlapped into a combination, a plurality of combinations are superimposed form the main body thermal-protective material then;
(2) the inside and outside surface with the main body thermal-protective material coats fabric, and is fixed-type.
2, space articulation as claimed in claim 1 mechanism is with the preparation method of heat preservation and insulation soft cover, and it is characterized in that: the described fabric that is coated on main body thermal-protective material outer surface is spliced by the polylith fabric, and seam crossing is through encapsulation process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100677106A CN100494758C (en) | 2007-03-20 | 2007-03-20 | Preparation metho of heat preservation and insulation soft cover used in space docking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100677106A CN100494758C (en) | 2007-03-20 | 2007-03-20 | Preparation metho of heat preservation and insulation soft cover used in space docking mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101038061A CN101038061A (en) | 2007-09-19 |
| CN100494758C true CN100494758C (en) | 2009-06-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007100677106A Expired - Fee Related CN100494758C (en) | 2007-03-20 | 2007-03-20 | Preparation metho of heat preservation and insulation soft cover used in space docking mechanism |
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| Country | Link |
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| CN (1) | CN100494758C (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2343183B1 (en) * | 2010-01-07 | 2015-07-22 | Armacell Enterprise GmbH & Co. KG | Elastomeric low temperature insulation |
| CN103016908B (en) * | 2012-12-13 | 2015-09-30 | 上海宇航系统工程研究所 | The soft cover of multilayer insulation of variable volume |
| CN103343861A (en) * | 2013-07-01 | 2013-10-09 | 中冶南方工程技术有限公司 | Heat insulation structure |
| JP6566376B1 (en) * | 2019-02-22 | 2019-08-28 | 三桜工業株式会社 | Pipe joint, tube with pipe joint, and method of manufacturing pipe joint |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4777086A (en) * | 1987-10-26 | 1988-10-11 | Owens-Corning Fiberglas Corporation | Low density insulation product |
-
2007
- 2007-03-20 CN CNB2007100677106A patent/CN100494758C/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4777086A (en) * | 1987-10-26 | 1988-10-11 | Owens-Corning Fiberglas Corporation | Low density insulation product |
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| Publication number | Publication date |
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| CN101038061A (en) | 2007-09-19 |
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| C14 | Grant of patent or utility model | ||
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Assignee: Hangzhou Fushida Special Material Co.,Ltd. Assignor: Ying Jianming Contract fulfillment period: 2009.6.8 to 2015.6.7 Contract record no.: 2009330001434 Denomination of invention: Preparation metho of heat preservation and insulation soft cover used in space docking mechanism Granted publication date: 20090603 License type: Exclusive license Record date: 20090617 |
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Free format text: EXCLUSIVE LICENSE; TIME LIMIT OF IMPLEMENTING CONTACT: 2009.6.8 TO 2015.6.7; CHANGE OF CONTRACT Name of requester: HANGZHOU FOSTER SPECIAL MATERIALS CO., LTD. Effective date: 20090617 |
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Owner name: HANGZHOU FUSHIDA SPECIAL MATERIAL CO., LTD. Free format text: FORMER OWNER: YING JIANMING Effective date: 20120131 |
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Effective date of registration: 20120131 Address after: 20, 310011 north of Gongshu District Concord village, Hangzhou, Zhejiang Patentee after: HANGZHOU FUSHIDA SPECIAL MATERIAL Co.,Ltd. Address before: 503, room 170, No. 52, Gongshu District Concord village, Zhejiang, Hangzhou 310011, China Patentee before: Ying Jianming |
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Address after: 311500, No. 178, Fengxiang Road, Tonglu Economic Development Zone, Tonglu County, Zhejiang, Hangzhou Patentee after: HANGZHOU FUSHIDA SPECIAL MATERIAL Co.,Ltd. Address before: 20, 310011 north of Gongshu District Concord village, Hangzhou, Zhejiang Patentee before: Hangzhou Fushida Special Material Co.,Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee |