CN202371383U - Reinforced multilayer heat-insulating material - Google Patents
Reinforced multilayer heat-insulating material Download PDFInfo
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- CN202371383U CN202371383U CN 201120509616 CN201120509616U CN202371383U CN 202371383 U CN202371383 U CN 202371383U CN 201120509616 CN201120509616 CN 201120509616 CN 201120509616 U CN201120509616 U CN 201120509616U CN 202371383 U CN202371383 U CN 202371383U
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Abstract
The utility model discloses a reinforced multilayer heat-insulating material, belonging to the technical field of thermal control of a spacecraft. The reinforced multilayer heat-insulating material comprises reflecting screens, reinforced materials and spacing materials, wherein the single reflecting screen and the single spacing material form a heat-insulating unit; N heat-insulating units are arranged sequentially from a first unit, a second unit to an Nth unit, and N is not more than 30; and the reinforced material is paved between the first unit and the second unit or between the second unit or the third unit. The reinforced materials have tensile strength of not less than 2.0 GPa, modulus of not more than 150 GPa and thickness of 200-300 microns, and the number of the layers is 2-8. The protective ability of tiny pieces of the multilayer heat-insulating material is improved by adding the reinforced material inside the ordinary multilayer heat-insulating material on the premise that the heat-insulating performance of the multilayer heat-insulating material is not reduced.
Description
Technical field
The utility model relates to a kind of enhancement mode multilayer insulation material, belongs to astrovehicle heat control technical field.
Background technique
Along with space junk, particularly diameter is less than the rapid increase of the small number of chips of 1mm, and low orbit spacecraft structure and device outer surface out of my cabin suffers the risk of small fragment bump to become big gradually.When small fragment clashes into out of my cabin structure and above deck equipment; Size, speed and angle etc. different according to the bump fragment; When collision acquires a certain degree, will form pit or hole above it, influence the proper functioning of instrument and equipment; Even possibly directly cause the damage of instrument and equipment, influence normally carrying out of aerial mission.
Consider that the cost of on astrovehicle, adding the conventional dedicated safeguard structure is bigger, adopt the design of the small fragment of special protection structural shielding very unrealistic.
Multilayer insulation material is owing to have fabulous heat-shielding performance; Add very light weight, mounting or dismounting convenient, do not have a dust and can be to characteristics such as surrounding environment pollute; One of the most basic means of astrovehicle passive heat control have been become; Be widely used in coated spacecraft module external structure and device outer surface, comprise the overwhelming majority of propellant tank, gas-liquid pipeline, electric wire and bulkhead etc.As the outer coating of structure and equipment out of my cabin, multilayer insulation material also will become the first road barrier of astrovehicle protection fragment bump.With respect to other design proposal of small fragment protective structure, realize that through the barrier propterty that strengthens multilayer insulation material the design of the small fragment protective of astrovehicle realizes that the most easily need not revise the spacecraft structure layout, cost is little, and application area is very extensive.
The foreign study personnel have realized the protection of the small fragment in the 1mm left and right sides through the way of the fragment protective ability of raising multilayer insulation material, and successfully are applied at the rail astrovehicle.
The common multilayer insulation material that present domestic astrovehicle adopts is made up of reflecting screen and Spacer, does not consider the fragment protective design.Consider that domestic and international astrovehicle has certain difference with the multilayer insulation material performance; External simultaneously domestic can't the acquisition of material that is used to strengthen the multilayer insulation material barrier propterty of adopting, it is just extremely important therefore to study the enhancement mode multilayer insulation material that is suitable for the small fragment protective design of China's astrovehicle.
Summary of the invention
1 purpose:
The purpose of the utility model provides a kind of enhancement mode multilayer insulation material, to overcome the deficiency of the small fragment protective design of astrovehicle, improves the fragment protective ability of multilayer insulation material.
For realizing above-mentioned purpose, the technological scheme of the utility model is following:
A kind of enhancement mode multilayer insulation material, said enhancement mode multilayer insulation material comprises reflecting screen, reinforced materials, interval insulant;
Wherein individual layer reflecting screen and individual layer interval insulant are formed an insulating unit, and N insulating unit is arranged in order, be followed successively by Unit 1, Unit 2 ... The N unit, N≤30; Between Unit 1 and Unit 2, or reinforced materials is applied in the shop between Unit 2 and Unit 3.
Tensile strength >=the 2.0GPa of said reinforced materials, modulus >=150GPa, preferred Kevlar129, thickness is 200～300 μ m, the number of plies is 2～8 layers.
Said reflecting screen is two-sided aluminized mylar, and thickness is 6～20 μ m.
Said interval insulant is nonmetal mesh material, and thickness is 10～20 μ m, preferred terylene net, specification 20～30D, 4 hole/cm of reticular density
2, full reeled yarn braiding.
Wherein, preferably at enhancement mode thermal-protective material outermost surface, promptly outer coating film is established on top layer, Unit 1, and reinforced materials is applied in the shop between Unit 1 and Unit 2.
Said outsourcing covering material is atomproof oxygen fire retardant or ITO film, and the thickness of said ITO film is 20～25 μ m.
Beneficial effect:
The utility model under the prerequisite that does not lower the multilayer insulation material heat-shielding performance, has improved the small fragment protective ability of multilayer insulation material through in the inner reinforced materials of adding of common multilayer insulation material.Hypervelocity impact test through common multilayer insulation material and the coated cellular board structure of enhancement mode multilayer insulation material is found; After in the common multilayer insulation material in Unit 20, filling 2 layers of Kevlar fabric; Under the stroke speed of 6.7km/s; The limit penetrates diameter and is increased to 1.50mm by 1.19mm, adds behind 5 layers of Kevlar the limit and penetrates increasing diameter and be added to 1.71mm.The utility model will be applied in * * the small fragment protective in satellite windward side on.
Description of drawings
Fig. 1 is described not with the structural representation of the enhancement mode multilayer insulation material of coated film for the utility model embodiment 1;
Fig. 2 is the structural representation of the described enhancement mode multilayer insulation material with coated film of the utility model embodiment 2;
Wherein, 1-reflecting screen, 2-enhancement mode material, 3-interval insulant, the outer coating film of 4-.
Embodiment
Describe the utility model in detail through specific embodiment below.
A kind of enhancement mode multilayer insulation material as shown in Figure 1, said enhancement mode multilayer insulation material comprises reflecting screen 1, reinforced materials 2, interval insulant 3;
Wherein individual layer reflecting screen 1 is formed an insulating unit with individual layer interval insulant 3, and 20 insulating units are arranged in order, be followed successively by Unit 1, Unit 2 ... Unit 20; Reinforced materials 2 is applied in the shop between Unit 2 and Unit 3.
Said reinforced materials 2 is Kevlar129, and for having the material than high-tensile and tensile modulus in the aramid fibre, thickness is 200 μ m, and the number of plies is 2 layers.
Said reflecting screen 1 is two-sided aluminized mylar, and thickness is 6 μ m.
Said interval insulant 3 is the terylene net, and thickness is 10 μ m, specification 20～30D, 4 hole/cm2 of reticular density, full reeled yarn braiding.
Wherein, the preparation process of enhancement mode multilayer insulation material is following:
Making the enhancement mode multilayer insulation material need experience reinforced materials 2 cuttings and enhancement mode multilayer insulation material and spread and cover and make two steps.
A. reinforced materials 2 shops are overlying on the plane cutting working station, make it keep nature smooth, avoid tensile buckling;
B. select the transparent non-setting adhesive band of peeling strength >=8N/25mm, tape width 20mm～30mm sticks on the position that needs cutting with adhesive tape along cutting line, compresses adhesive tape in Vertical direction in the taping process, does not make reinforced materials 2 distortion in the compaction process.
C. use scissors or cut-off knife cutting, the position of cutting apart with a knife or scissors must not produce horizontal cut.During cutting, answer the fiber of disposable severing reinforced materials 2, otherwise will produce more silk hair.
D. after cutting finishes, the transparent non-setting adhesive band is peeled off along the cutting direction, stripping process should be slow; Do not make reinforced materials 2 produce bigger distortion, observe whether wire drawing simultaneously, if the wire drawing phenomenon is arranged; Should stop to peel off, continue again to peel off cut off the silk hair of wire drawing with scissors after.
E. after peeling off the transparent non-setting adhesive band, reinforced materials 2 is paved, paste edge sealing with polyester film adhesive tape or Kapton Tape.
Enhancement mode multilayer insulation material shop is covered and is made and adopt the multilayer insulation material shop to cover and the common process of sewing tech, and the superimposed back of multilayer material is made with fire-retardant line or polyester thread.But note when suture needle penetrates multilayer insulation material, should avoid applying transverse force as far as possible.
A kind of enhancement mode multilayer insulation material as shown in Figure 2, said enhancement mode multilayer insulation material comprises reflecting screen 1, reinforced materials 2, interval insulant 3;
Wherein individual layer reflecting screen 1 is formed an insulating unit with individual layer interval insulant 3, and N insulating unit is arranged in order, be followed successively by Unit 1, Unit 2 ... Unit 15; At enhancement mode thermal-protective material outermost surface, promptly outer coating film 4 is established on top layer, Unit 1, and reinforced materials 2 is applied in the shop between Unit 1 and Unit 2.
Said reinforced materials 2 is Kevlar129, and thickness is 300 μ m, and the number of plies is 2 layers.
Said reflecting screen 1 is two-sided aluminized mylar, and thickness is 6 μ m.
Said interval insulant 3 is the terylene net, and thickness is 20 μ m.
Said outer coating film 4 materials are atomproof oxygen fire retardant or ITO film.
The preparation process of said enhancement mode multilayer insulation material is identical with embodiment 1.
Hypervelocity impact test through common multilayer insulation material and the coated cellular board structure of enhancement mode multilayer insulation material is found; After in the common multilayer insulation material in Unit 20, filling 2 layers of Kevlar fabric; Under the stroke speed of 6.7km/s; The limit penetrates diameter and is increased to 1.50mm by 1.19mm, adds behind 5 layers of Kevlar the limit and penetrates increasing diameter and be added to 1.71mm.
In sum, more than being merely the preferred embodiment of the utility model, is not the protection domain that is used to limit the utility model.All within the spirit and principle of the utility model, any modification of being done, be equal to replacement, improvement etc., all should be included within the protection domain of the utility model.
Claims (6)
1. enhancement mode multilayer insulation material, it is characterized in that: said enhancement mode multilayer insulation material comprises reflecting screen (1), reinforced materials (2), interval insulant (3);
Wherein individual layer reflecting screen (1) and individual layer interval insulant (2) are formed an insulating unit, and N insulating unit is arranged in order, be followed successively by Unit 1, Unit 2 ... The N unit, N≤30; Between Unit 1 and Unit 2, or reinforced materials (2) is applied in the shop between Unit 2 and Unit 3;
Tensile strength >=the 2.0GPa of said reinforced materials (2), modulus >=150GPa, thickness are 200 ~ 300 μ m, and the number of plies is 2 ~ 8 layers;
Said reflecting screen (1) is two-sided aluminized mylar, and thickness is 6 ~ 20 μ m;
Said interval insulant (3) is nonmetal mesh material, and thickness is 10 ~ 20 μ m.
2. a kind of enhancement mode multilayer insulation material according to claim 1 is characterized in that: said reinforced materials (2) is Kevlar129.
3. a kind of enhancement mode multilayer insulation material according to claim 1 is characterized in that: said interval insulant (3) is the terylene net, specification 20 ~ 30D, 4 hole/cm of reticular density
2, full reeled yarn braiding.
4. a kind of enhancement mode multilayer insulation material according to claim 1 is characterized in that: at enhancement mode thermal-protective material outermost surface, promptly outer coating film (4) is established on top layer, Unit 1, and reinforced materials (2) is applied in the shop between Unit 1 and Unit 2.
5. a kind of enhancement mode multilayer insulation material according to claim 4 is characterized in that: said outer coating film (4) material is atomproof oxygen fire retardant or ITO film.
6. a kind of enhancement mode multilayer insulation material according to claim 5 is characterized in that: the thickness of said ITO film is 20 ~ 25 μ m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120509616 CN202371383U (en) | 2011-12-08 | 2011-12-08 | Reinforced multilayer heat-insulating material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120509616 CN202371383U (en) | 2011-12-08 | 2011-12-08 | Reinforced multilayer heat-insulating material |
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| Publication Number | Publication Date |
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| CN202371383U true CN202371383U (en) | 2012-08-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201120509616 Expired - Lifetime CN202371383U (en) | 2011-12-08 | 2011-12-08 | Reinforced multilayer heat-insulating material |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103984192A (en) * | 2014-05-29 | 2014-08-13 | 中国科学院光电技术研究所 | Space camera and achieving method thereof suitable for deep space exploration high-temperature work environment |
| CN105109709A (en) * | 2015-08-25 | 2015-12-02 | 中国人民解放军国防科学技术大学 | Thermal insulation/protection integrated space debris protection structure and application thereof |
| CN106113848A (en) * | 2016-06-22 | 2016-11-16 | 上海交通大学 | It is applied to the spatial multi punching heat-barrier material of space thin-walled deployable structure Thermal protection |
| CN106467177A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | Substitute the method for satellite side plate and be applied to the multiple structure substituting satellite side plate |
| CN106481932A (en) * | 2016-09-08 | 2017-03-08 | 上海卫星工程研究所 | Wave transparent type multilayer insulation material structure and preparation method |
| CN111207270A (en) * | 2020-03-11 | 2020-05-29 | 山东建筑大学 | Vacuum insulation panel containing heat radiation shielding film |
-
2011
- 2011-12-08 CN CN 201120509616 patent/CN202371383U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103984192A (en) * | 2014-05-29 | 2014-08-13 | 中国科学院光电技术研究所 | Space camera and achieving method thereof suitable for deep space exploration high-temperature work environment |
| CN105109709A (en) * | 2015-08-25 | 2015-12-02 | 中国人民解放军国防科学技术大学 | Thermal insulation/protection integrated space debris protection structure and application thereof |
| CN106113848A (en) * | 2016-06-22 | 2016-11-16 | 上海交通大学 | It is applied to the spatial multi punching heat-barrier material of space thin-walled deployable structure Thermal protection |
| CN106467177A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | Substitute the method for satellite side plate and be applied to the multiple structure substituting satellite side plate |
| CN106481932A (en) * | 2016-09-08 | 2017-03-08 | 上海卫星工程研究所 | Wave transparent type multilayer insulation material structure and preparation method |
| CN111207270A (en) * | 2020-03-11 | 2020-05-29 | 山东建筑大学 | Vacuum insulation panel containing heat radiation shielding film |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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Granted publication date: 20120808 |
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| CX01 | Expiry of patent term |