CN106675391B - Radiation protection thermal control coating and its manufacturing method - Google Patents
Radiation protection thermal control coating and its manufacturing method Download PDFInfo
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- CN106675391B CN106675391B CN201510766078.9A CN201510766078A CN106675391B CN 106675391 B CN106675391 B CN 106675391B CN 201510766078 A CN201510766078 A CN 201510766078A CN 106675391 B CN106675391 B CN 106675391B
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Abstract
The invention discloses a kind of radiation protection thermal control coatings, and the coating is using low atomic number material as the surface covering of thermal control coating, inter coat of the middle atomic number material as thermal control coating, primer coating of the high atomic number material as thermal control coating.Coating of the invention, under same surface density, compared with ZnO coating, 10% or more radiation protection capability improving, and coating solar absorptance α s is about 0.152, thermal emissivity ε is about 0.886, suitable with ZnO white paint.
Description
Technical field
The invention belongs to spacecraft space environmental projects and thermal control technical field, specifically, the present invention relates to one kind to prevent
Radiate thermal control coating and its manufacturing method.
Background technique
Tatal ionizing dose effects caused by space radiation environment are the main reason for single machine and device are damaged on star.Space
Ionising radiation accumulated dose generates during being mainly derived from radiation zone electron radiation, the radiation of sun high energy proton and electron radiation
Bremstrahlen.
Theoretically, any material all has radiation proof function, can be complete by radiation as long as material thickness is enough
Shielding.But for satellite, the means of defence after this unlimited increase is infeasible.If can use existing material on star
Material, is improved, improves its protective capacities to space radiation environment, then can be mentioned under the premise of not increasing weight
The protective benefits to single machine, device in star are risen, thus the reliability of satellite in orbit.
Radiation protection research is it has been shown that material is closely related to radiation proof protective capacities and atom in material.It is former
The high atom pair electronics of sub- ordinal number and x-ray protective performance are high, still, the bremstrahlen amount generated during electron impact
Also big；Conversely, the atom of low atomic number, although poor to electronics and x-ray protective performance, during electron impact
The bremstrahlen amount of generation is small.
Fig. 1 gives under geostationary orbit, dose of radiation with radiation shield (Al) thickness change curve.Therefrom may be used
To find out, after the shielding of about 10mm equivalent thickness of aluminium, the main radiation environment of inside satellite has been bremstrahlen.And the knot of satellite
Structure, surface functional material etc., thickness generally will be more than 10mm, can generate shielding action to space radiation environment.It is possible thereby to
Find out, for space radiating particle after being incident on satellite, the bremstrahlen of generation is single machine in star, component generation radiation injury
The main reason for.Protection to bremstrahlen is to the emphasis that single machine, device protect in star.
Therefore, to the radiation protection in star there are two approach, first is that the protection to star inner bremsstrahlung, the other is in source
The yield of bremstrahlen is reduced on head.
In general, white paint is a kind of satellite commonly thermal control coating, its main feature is that solar absorptance is low, thermal emissivity is high.It defends
Star white paint is mostly using ZnO as pigment, such as S781 white paint.Thermal control coating is due to playing space particle radiation in satellite surface
Important shielding action.Due to the Zn atom in ZnO, although good inhibition can be played to electron-proton, by
It is big in its atomic number, therefore, unavoidably generate a large amount of bremstrahlens.
For this reason, it is necessary to seek a kind of thermal control coating, to solve a variety of radiation in space radiation environment.
Summary of the invention
Based on this, the present invention is based on composite shielding preventing principles, propose a kind of heat of longitudinal atomic number gradients distribution
Coating structure is controlled, most surface layer utilizes low atomic number material, and to reduce bremstrahlen to the greatest extent, middle layer uses the larger material of atomic number
Material, shields electronics and bremstrahlen ray, and innermost layer uses high atomic number material, reinforces to bremstrahlen ray
It absorbs.Thermal control coating of the invention can meet except existing white paint class thermal control coating thermal control performance requirement, promote coating pair
The performance of space radiation environment protection.
Present invention employs the following technical solutions:
A kind of radiation protection thermal control coating, wherein using low atomic number material as the surface covering of thermal control coating, Central Plains
Inter coat of the sub- ordinal number material as thermal control coating, primer coating of the high atomic number material as thermal control coating.
Wherein, the gold of primer coating Zr, Ba, Bi (other close atomic numbers or the high metal of atomic number also can)
Belong to oxide coating；Inter coat is ZnO coating；Surface covering is BN coating, and Al2O3 coating also may be used.
Wherein, primer coating with a thickness of 0.01mm to 0.5mm；Inter coat with a thickness of 0.01mm to 0.5mm；Surface
Coating with a thickness of 0.01mm to 0.5mm.
Wherein, the metal oxide of Zr, Ba, Bi are ZrO2, BaO or Bi2O3。
A kind of manufacturing method of above-mentioned radiation protection thermal control coating, includes the following steps:
1 by zirconium oxide or oxidation titanate particle and silicon resin adhesive according to weight ratio 1:4 to 2:1 after mixing, spray
It is coated in substrate, coating thickness 0.01mm to 0.5mm, solidifies formation primer coating in 12-16 hours；
2 by Zinc oxide particles and silicon resin adhesive according to weight ratio 1:4 to 2:1 after mixing, be sprayed on bottom painting
On layer, coating thickness 0.01mm to 0.5mm solidifies 12-16 hours formation inter coats；
3 by boron nitride particle and silicon resin adhesive according to weight ratio 1:4 to 2:1 after mixing, be sprayed on intermediate painting
On layer, coating thickness 0.05mm to 0.5mm solidification 24 hours or more, completes coating.
Wherein, substrate is the exemplar for needing to coat the low high thermal emissivity white coating of solar absorptance.
A kind of structural member in space radiation environment, Surface mulch have above-mentioned radiation protection thermal control coating.
The present invention improves on ZnO off-white color thermal control coating basis, and single ZnO coating is done hierarchical design,
Surface layer uses BN white coating, and middle layer remains unchanged still for ZnO coating, and bottom is using the painting of the metal oxides such as Zr, Ba, Bi
Layer.Surface layer utilizes BN coating, it is possible to reduce the bremstrahlen amount that charged particle generates during being absorbed, middle layer and bottom
Absorption to bremstrahlen can be increased using high atomic number material.Under same surface density, compared with pure ZnO coating, radiation
Protective capacities promotes 10% or more.And coating solar absorptance α s is about 0.152, thermal emissivity ε is about 0.886, with ZnO white paint
Quite.
Detailed description of the invention
Fig. 1 gives under geostationary orbit, dose of radiation with radiation shield (Al) thickness change curve.
Fig. 2 is the structural schematic diagram of radiation protection thermal control coating of the invention.
In figure: 1- substrate, 2- primer coating, 3- middle layer, 4- surface covering.
Specific embodiment
The structure of radiation protection thermal control coating of the invention is further described with reference to the accompanying drawing.
Referring to fig. 2, Fig. 2 is the structural schematic diagram of radiation protection thermal control coating of the invention, the thermal control coating include substrate with
And the successively primer coating 2 of spraying setting on the base 1, low atomic number is utilized in inter coat 3 and surface covering 4, the coating
The surface covering of number material, the inter coat of middle atomic number material, the primer coating of high atomic number material.
Embodiment 1
ZrO2 bottom, ZnO middle layer, BN surface covering
After mixing according to weight ratio 1:2 by zirconia particles and silicon resin adhesive, it is sprayed on Al2O3In substrate, spray
Thickness 0.1mm is applied, is solidified 12 hours；Then by Zinc oxide particles and silicon resin adhesive according to weight ratio 1:2 after mixing,
It is sprayed in substrate, coating thickness 0.1mm, solidifies 16 hours；Finally by boron nitride particle and silicon resin adhesive according to weight
It after more uniform than 1:2, is sprayed in substrate, coating thickness 0.1mm, after solidification 24 hours, completes coating.
By measurement, measuring solar absorptance α s is about 0.152, and thermal emissivity ε is about 0.886, suitable with ZnO white paint,
It is suitable with S781 white paint.It is calculated using Casino electron impact simulation softwares, under same surface density, this method can be mentioned
High 10% or more radiation protection ability.
2 BaO bottom of embodiment, ZnO middle layer, BN surface covering
After mixing according to weight ratio 1:4 by oxidation titanate particle and silicon resin adhesive, it is sprayed on SiO2In substrate, spray
Thickness 0.3mm is applied, is solidified 16 hours；Then by Zinc oxide particles and silicon resin adhesive according to weight ratio 1:4 after mixing,
It is sprayed in substrate, coating thickness 0.3mm, solidifies 20 hours；Finally by boron nitride particle and silicon resin adhesive according to weight
It after more uniform than 1:4, is sprayed in substrate, coating thickness 0.05mm, after solidification 24 hours, completes coating.
By measurement, measuring solar absorptance α s is about 0.150, and thermal emissivity ε is about 0.891, suitable with ZnO white paint,
It is suitable with S781 white paint.It is calculated using Casino electron impact simulation softwares, under same surface density, this method can be mentioned
High 8% or more radiation protection ability.
3 Bi of embodiment2O3Bottom, TiO2Middle layer, BN surface covering
After mixing according to weight ratio 2:1 by Bismuth oxide particles and silicon resin adhesive, it is sprayed on SiO2In substrate, spray
Thickness 0.5mm is applied, is solidified 16 hours；Then by titan oxide particles and silicon resin adhesive according to weight ratio 1:2 after mixing,
It is sprayed in substrate, coating thickness 0.5mm, solidifies 20 hours；Finally by boron nitride particle and silicon resin adhesive according to weight
It after more uniform than 1:2, is sprayed in substrate, coating thickness 0.3mm, after solidification 24 hours, completes coating.
By measurement, measuring solar absorptance α s is about 0.155, and thermal emissivity ε is about 0.881, suitable with ZnO white paint,
It is suitable with S781 white paint.It is calculated using Casino electron impact simulation softwares, under same surface density, this method can be mentioned
High 14% or more radiation protection ability.
The present invention proposes the thermal control coating structure of longitudinal sub- ordinal number gradient distribution, and surface layer uses the material of low atomic number,
To reduce the generation of bremstrahlen to the greatest extent, middle layer and bottom gradually adopt the material of high atomic number, to absorb incidence as far as possible
Electronics and bremstrahlen ray.To the dose of radiation for reducing inside satellite single machine, receiving on device.
The structural member used in the case where coating the space environment after above-mentioned coating, most of radiating particle can be defended in space
Star surface functional material, structure etc. absorb, thus will not influence single machine in star, device, and particle generates during being absorbed
Bremstrahlen can then pass through satellite functional material, structure etc., total dose effect is generated to single machine, device in star.
Although giving detailed description and explanation to specific implementation of the patent mode above, it should be noted that
We can the conception of patent according to the present invention various equivalent changes and modification are carried out to above embodiment, such as two layers of coatings or
The design of three layers of person or more coatings should all when the spirit that generated function is still covered without departing from specification and attached drawing
Within the protection scope of this patent.
Claims (6)
1. radiation protection thermal control coating, wherein using low atomic number material as the surface covering of thermal control coating, middle atomic number
Inter coat of the material as thermal control coating, primer coating of the high atomic number material as thermal control coating, wherein primer coating
For the coating of metal oxides of Zr, Ba, Bi；Inter coat is ZnO coating；Surface covering is BN coating or Al2O3Coating.
2. radiation protection thermal control coating as described in claim 1, wherein primer coating with a thickness of 0.01mm to 0.5mm；It is intermediate
Coating with a thickness of 0.01mm to 0.5mm；Surface covering with a thickness of 0.01mm to 0.5mm.
3. the radiation protection thermal control coating as described in claim 1-2 any one, wherein the metal oxide of Zr, Ba, Bi is
ZrO2, BaO or Bi2O3。
4. the manufacturing method of any one of the claim 1-3 radiation protection thermal control coating, includes the following steps:
1) by zirconium oxide or oxidation titanate particle and silicon resin adhesive according to weight ratio 1:4 to 2:1 after mixing, be sprayed on
In substrate, coating thickness 0.05mm to 0.5mm solidifies formation primer coating in 12-16 hours；
2) by Zinc oxide particles and silicon resin adhesive according to weight ratio 1:4 to 2:1 after mixing, be sprayed on primer coating
On, coating thickness 0.05mm to 0.5mm solidifies 12-16 hours formation inter coats；
3) by boron nitride particle and silicon resin adhesive according to weight ratio 1:4 to 2:1 after mixing, be sprayed on inter coat
On, coating thickness 0.05mm to 0.5mm solidification 24 hours or more, completes coating.
5. manufacturing method as claimed in claim 4, wherein substrate is to need to coat the low high thermal emissivity white of solar absorptance
The exemplar of coating.
6. Surface mulch has the right to require the described in any item radiation protection heat of 1-3 for the structural member in space radiation environment
Control coating.
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| CN108546458B (en) * | 2018-05-17 | 2020-06-12 | 哈尔滨工业大学 | Composite coating with photothermal conversion capability capable of changing along with environmental temperature and preparation method thereof |
| CN108860664B (en) * | 2018-06-20 | 2020-07-14 | 上海卫星工程研究所 | Novel thermal control device for space flexible mechanism |
| CN109504963B (en) * | 2018-12-20 | 2020-08-18 | 兰州空间技术物理研究所 | Anti-radiation solid lubricating coating and preparation method thereof |
| CN110697088B (en) * | 2019-10-15 | 2020-05-19 | 中国科学院云南天文台 | Thermal control coating for sun-facing surface of spacecraft thermal shield |
| CN111393882B (en) * | 2020-03-24 | 2021-09-28 | 哈尔滨工业大学 | Ultraviolet radiation resistant low-absorptivity inorganic white thermal control coating and preparation method thereof |
| US11858613B2 (en) * | 2020-11-23 | 2024-01-02 | General Electric Company | Aerospace vehicles with coatings for heat radiation and associated methods |
| CN114149740B (en) * | 2021-11-30 | 2022-09-27 | 北京卫星制造厂有限公司 | Radiation protection coating and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1446730A (en) * | 2003-03-07 | 2003-10-08 | 上海大学 | Radiation hardening shield method |
| JP2004020414A (en) * | 2002-06-18 | 2004-01-22 | Mitsubishi Heavy Ind Ltd | Shield structure and space structure having the same |
| CN1585036A (en) * | 2004-06-10 | 2005-02-23 | 上海交通大学 | Composite coating with radiation-proof perforance function |
| CN102479562A (en) * | 2010-11-25 | 2012-05-30 | 上海交通大学医学院附属第三人民医院 | Anti-radiation material |
| CN102490913A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Anti-total-dose shielding device |
| CN103832599A (en) * | 2012-11-27 | 2014-06-04 | 中国科学院空间科学与应用研究中心 | Composite shielding method for satellite to resist total dose effect |
| CN104962128A (en) * | 2015-06-09 | 2015-10-07 | 上海卫星工程研究所 | Preparation and coating method of total dose radiation shielding coating layer material |
-
2015
- 2015-11-11 CN CN201510766078.9A patent/CN106675391B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004020414A (en) * | 2002-06-18 | 2004-01-22 | Mitsubishi Heavy Ind Ltd | Shield structure and space structure having the same |
| CN1446730A (en) * | 2003-03-07 | 2003-10-08 | 上海大学 | Radiation hardening shield method |
| CN1585036A (en) * | 2004-06-10 | 2005-02-23 | 上海交通大学 | Composite coating with radiation-proof perforance function |
| CN102479562A (en) * | 2010-11-25 | 2012-05-30 | 上海交通大学医学院附属第三人民医院 | Anti-radiation material |
| CN102490913A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Anti-total-dose shielding device |
| CN103832599A (en) * | 2012-11-27 | 2014-06-04 | 中国科学院空间科学与应用研究中心 | Composite shielding method for satellite to resist total dose effect |
| CN104962128A (en) * | 2015-06-09 | 2015-10-07 | 上海卫星工程研究所 | Preparation and coating method of total dose radiation shielding coating layer material |
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