CN104962128A - Preparation and coating method of total dose radiation shielding coating layer material - Google Patents
Preparation and coating method of total dose radiation shielding coating layer material Download PDFInfo
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- CN104962128A CN104962128A CN201510314078.5A CN201510314078A CN104962128A CN 104962128 A CN104962128 A CN 104962128A CN 201510314078 A CN201510314078 A CN 201510314078A CN 104962128 A CN104962128 A CN 104962128A
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Abstract
The invention discloses a preparation and coating method of a total dose radiation shielding coating layer material. The method concretely comprises the following steps: uniformly mixing a high atomic number material with a high-molecular polymer to obtain a mixed coating A; uniformly mixing a low atomic number material with the high-molecular polymer to obtain a mixed coating B; and coating the mixed coating A on the surface layer of a device shell in order to form a high atomic number material layer, and coating the mixed coating B on the surface of the high atomic number material layer to form a low atomic number material layer. The method for preparing the total dose radiation shielding coating layer material and coating the inner wall of the product shell allows the coating layer of the coating layer material to stand up the emission stage of a spacecraft and in-orbit space environment, and the coating layer greatly improves the space total dose radiation environment resistance of the coated product.
Description
Technical field
The present invention relates to aerospacecraft resistant to total dose shielding field, particularly a kind of preparation of resistant to total dose curtain coating material and coating method.
Background technology
Spacecraft is when too airflight, Space heavy ion in space environment and high energy particle are absorbed by components and parts, rest in components and parts, along with the increase of total amount, the function of spacecraft and performance can be caused to decay gradually along with the increase of time, finally cause spacecraft cisco unity malfunction, have a strong impact on work-ing life and the reliability of spacecraft, this situation is called as total dose effect.Resistant to total dose reinforcement measure is called as to the measure that components and parts process to slow down or avoid this phenomenon to occur.It is generally paste the heavy metal material such as sheet lead or tantalum skin at component surface that existing resistant to total dose reinforces the method taked.In the example of shown in Fig. 1, the device that will be positioned at circuit card to does resistant to total dose and reinforces, and existing method is by heavy metal materials such as binding wire colligation sheet lead or tantalum skins on the surface of described device.Also sheet lead or tantalum skin can be placed in the surface of components and parts in the mode of pasting, thus realize the protection to components and parts.
This method of the prior art also exists obvious defect: because heavy metal material is directly applied in component surface, under Space heavy ion in space environment and the effect of high energy particle, easily there is nuclear reaction and produce secondary particle (i.e. bremsstrahlung problem) in these heavy metal materials, this may cause even more serious radiation problem, satellite cisco unity malfunction can be caused when situation is serious, have a strong impact on satellite work-ing life and reliability.In addition, along with the continuous progress of technology, the volume of components and parts is more and more less, by also increasing for the difficulty that sheet lead or tantalum skin are pasted onto component surface.Therefore, this method cannot meet the needs of modern spacecraft development.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of preparation and coating method of resistant to total dose curtain coating material.Problem to be solved by this invention is the bremsstrahlung problem overcoming above-mentioned existing reinforcement material existence, thus provide one can solve bremsstrahlung problem, the preparation of the curtain coating material that resistant to total dose effect is better and the coating method of raising coated material cohesive force.
The present invention is achieved by the following technical solutions:
The invention provides a kind of preparation and coating method of resistant to total dose curtain coating material, specifically comprise the steps:
High atomic number material is mixed to obtain compo A with high molecular polymer;
Low atomic number material is mixed to obtain compo B with high molecular polymer;
First compo A is coated in device shell inwall top layer, forms high atomic number material layer, then at described high atomic number material surface application bed of material compo B, form low atomic number material layer.
Preferably, the thickness sum of described high atomic number material layer and described low atomic number material layer is no more than 0.5mm.
More preferably, the thickness of described high atomic number material layer is 0.2 ~ 0.3mm; The thickness of described low atomic number material layer is 0.15 ~ 0.2mm; The thickness more preferably 0.20mm of described high atomic number material layer.
Preferably, in described compo A, high atomic number material is 3:1 with the ratio of the density of low atomic number material in described compo B.
Preferably, described high atomic number material comprises tantalum powder, barium powder, osmium powder, iridium powder, platinum powder, bronze or tungsten powder.
Preferably, described low atomic number material comprises silica flour, copper powder or nickel powder.
Preferably, described high molecular polymer comprises purifying silicon rubber, urethane, polyethylene, epoxy resin or polyimide.
More preferably, described high molecular polymer is purifying silicon rubber, and purifying silicon rubber is a kind of silicon rubber meeting spacecraft use, and its total mass loss is the service requirements meeting spacecraft common product with coagulating volatile matter, namely total mass loss is not more than 1%, can coagulate volatile matter and be not more than 0.1%.
Preferably, described method also comprises, and before coating compo A, gridding is carried out on device shell inwall top layer and divides; In order to improve the cohesive force of coating on product, and be coated on the casing inner wall of product, and need the casing inner wall of product to carry out stress and strain model, the size of stress and strain model is no more than 20 × 20cm
2can adjust according to the size of variant production, cohesive strength, through theoretical analysis and ground experiment checking, coated material is through coating bonding process and the stress and strain model with casing, can meet the service requirements of product, simultaneously coated material can the total radiation dose ability of the anti-space environment of raising product by a relatively large margin.
Compared with prior art, the present invention has following beneficial effect: adopt and instant invention overcomes because heavy metal material is directly applied in component surface, under the effect such as Space heavy ion and high energy particle, there is nuclear reaction and produce secondary particle (bremsstrahlung), even more serious radiation problem may be caused, simultaneously by changing the configuration of the casing inner wall of product, improve the cohesive strength of coated material, solve coated material coming off or the generation of crack performance in test and use procedure.Product resistant to total dose ability on aerospacecraft is got a promotion, effectively improves satellite life and reliability.Can be widely used on aerospacecraft, particularly geo-synchronous orbit satellite, resistant to total dose shield effectiveness is better.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is prior art schematic diagram;
Fig. 2 is STRUCTURE DECOMPOSITION schematic diagram of the present invention;
Fig. 3 is that the present invention applies pictorial diagram;
Wherein, 1 is circuit card, and 2 is sheet lead or tantalum skin etc., and 3 is devices, and 4 is binding wires, and 5 is that 6 is the first layer aluminum substrates, and 7 is second layer tungsten powder layers, and 8 is third layer nickel powder layers by shielding components and parts; A, b, c are the pictorial diagram that different gridding divides rear coating.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
With reference to figure 2, in the preparation of resistant to total dose curtain coating material of the present invention and coating method, the composition of coating is tungsten powder and nickel powder is 3:1 according to area density ratio, wherein, tungsten powder layer thickness is about 0.20 ~ 0.30mm, nickel powder layer thickness is 0.15 ~ 0.20mm, and total thickness is 0.35 ~ 0.50mm, carries out mix and blend by purifying silicon rubber.
The effect of the first layer is that the ionization stopping power utilizing low atomic number material larger comes slowing down and shielding primary electron.This layer is made up of low atomic number material, and it have employed aluminum in the present embodiment, and can adopt magnesium alloy, aluminum magnesium alloy or lithium magnesium alloy etc. material in other embodiments.In actual applications, the first low atomic number layer can directly in the spacecraft such as unit casing existing parts realize.The first layer, the thickness of low atomic number layer is generally between 1mm to 3mm.In order to alleviate the oeverall quality of spacecraft, as the preferred implementation of one, the spacecraft that have employed shielding unit of the present invention can reduce the thickness of casing, as reduced to 1mm by 3mm, but still can reach the shield effectiveness that the more former casing of resistant to total dose screening ability is significantly improved.
The second layer, the effect of high atomic number layer is the scattering cross-section scattered electrons effectively utilizing high atomic number material larger, and absorbs secondary bremsstrahlung photons.This layer is made up of high atomic number material, and in the present embodiment, described high atomic number layer have employed tungsten material and realizes, but in other embodiments, also can adopt the materials such as such as tantalum, barium, osmium, iridium, platinum and gold.The thickness of described high atomic number layer between 0.20 ~ 0.30mm, preferred 0.20mm.
Third layer, the effect of low atomic number layer absorbs the photoelectron and backscattered electron that produce in high atomic number material, the secondary light electron emission that simultaneously X-ray and material effects can be suppressed to produce and electron backscattered.This layer is made up of low atomic number material, have employed nickel material in the present embodiment, and can adopt above the material such as such as silicon, copper etc. mentioned in other embodiments.The thickness of the second low atomic number layer is generally greater than secondary photoelectronic range, and its scope is between 0.15 ~ 0.20mm.The thickness sum of described high atomic number layer and the second low atomic number layer is generally no more than 0.5mm, proves through experiment, and this thickness can make to reach a balance preferably between the quality of shielding unit and shield effectiveness.
High molecular polymer can be adopted to bond as tackiness agent between each screen layer above-mentioned, described high molecular polymer is as purifying silicon rubber, urethane, polyethylene, epoxy resin, polyimide etc.
Above-mentioned screen layer is coated on unit casing inner wall, the configuration of inwall is also key one ring affecting coating stability, by carrying out stress and strain model to unit casing inner wall, reduce the surface covered of coated material, increase the cohesive strength of coating and casing, meet spacecraft testing requirement (as shown in Figure 3).
The mode that the present invention takes is that multiple material utilizes ordination number different, to Energetic particle, particularly high-energy electron utilizes the mechanism of complementary absorption, Anti-total-dose shielding device is implemented in complete machine (instrument) level, in order to realize the bonding between different screen layer, adopt with instrument casing (being generally Al) as matrix, taking high molecular polymer as tackiness agent (as purifying silicon rubber, urethane, polyethylene, epoxy resin, polyimide etc.), take metal (or nonmetal) particle as the resistant to total dose curtain coating material of filler.Macromolecular material itself also has good radiation shielding performance to heavy ions such as protons simultaneously.By high atomic number and low atomic number coating on instrument casing, can under the prerequisite of reduce engine thickness of the shell (reducing to 1mm by 3mm), reach the shield effectiveness that the more former casing of resistant to total dose screening ability is significantly improved, effectively improve satellite reliability.Can be widely used on aerospacecraft, particularly geo-synchronous orbit satellite, resistant to total dose shield effectiveness is better.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. the preparation of resistant to total dose curtain coating material and a coating method, is characterized in that, specifically comprise the steps:
High atomic number material is mixed to obtain compo A with high molecular polymer;
Low atomic number material is mixed to obtain compo B with high molecular polymer;
First compo A is coated in device shell inwall top layer, forms high atomic number material layer, then at described high atomic number material layer surface application compo B, form low atomic number material layer.
2. the preparation of resistant to total dose curtain coating material according to claim 1 and coating method, it is characterized in that, the thickness sum of described high atomic number material layer and described low atomic number material layer is no more than 0.5mm.
3. the preparation of resistant to total dose curtain coating material according to claim 2 and coating method, it is characterized in that, the thickness of described high atomic number material layer is 0.2 ~ 0.3mm; The thickness of described low atomic number material layer is 0.15 ~ 0.2mm.
4. the preparation of resistant to total dose curtain coating material according to claim 1 and coating method, it is characterized in that, in described compo A, high atomic number material is 3:1 with the ratio of the density of low atomic number material in described compo B.
5. the preparation of the resistant to total dose curtain coating material according to claim 1 or 4 and coating method, is characterized in that, described high atomic number material comprises tantalum powder, barium powder, osmium powder, iridium powder, platinum powder, bronze or tungsten powder.
6. the preparation of the resistant to total dose curtain coating material according to claim 1 or 4 and coating method, it is characterized in that, described low atomic number material comprises silica flour, copper powder or nickel powder.
7. the preparation of the resistant to total dose curtain coating material according to claim 1 or 4 and coating method, it is characterized in that, described high molecular polymer comprises purifying silicon rubber, urethane, polyethylene, epoxy resin or polyimide.
8. the preparation of resistant to total dose curtain coating material according to claim 1 and coating method, it is characterized in that, described method also comprises, and before coating compo A, gridding is carried out on device shell inwall top layer and divides.
9. the preparation of the resistant to total dose curtain coating material according to claim 1 or 8 and coating method, is characterized in that, the width at described stress and strain model place is greater than 1mm.
10. the preparation of the resistant to total dose curtain coating material according to claim 1 or 8 and coating method, it is characterized in that, described method also comprises, and before coating compo A, described device thickness of the shell is thinned to 1mm.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105738936A (en) * | 2016-02-25 | 2016-07-06 | 北京卫星环境工程研究所 | Space radiation environment and effect combination detection structure |
| CN106098127A (en) * | 2016-06-06 | 2016-11-09 | 南京航空航天大学 | There is flexible radiation protection material radiating warning and temp regulating function and preparation method thereof |
| CN106675391A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Radiation-proof thermal control coating and manufacturing method thereof |
| CN114149740A (en) * | 2021-11-30 | 2022-03-08 | 北京卫星制造厂有限公司 | Radiation protection coating and preparation method thereof |
| CN117810207A (en) * | 2023-12-29 | 2024-04-02 | 深圳市安信达存储技术有限公司 | Metal sheet packaging method of embedded memory chip in space environment satellite |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1446730A (en) * | 2003-03-07 | 2003-10-08 | 上海大学 | Radiation hardening shield method |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1446730A (en) * | 2003-03-07 | 2003-10-08 | 上海大学 | Radiation hardening shield method |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106675391A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Radiation-proof thermal control coating and manufacturing method thereof |
| CN106675391B (en) * | 2015-11-11 | 2019-03-05 | 北京卫星环境工程研究所 | Radiation protection thermal control coating and its manufacturing method |
| CN105738936A (en) * | 2016-02-25 | 2016-07-06 | 北京卫星环境工程研究所 | Space radiation environment and effect combination detection structure |
| CN105738936B (en) * | 2016-02-25 | 2019-04-09 | 北京卫星环境工程研究所 | Space radiation environment and effect combination detecting structure |
| CN106098127A (en) * | 2016-06-06 | 2016-11-09 | 南京航空航天大学 | There is flexible radiation protection material radiating warning and temp regulating function and preparation method thereof |
| CN106098127B (en) * | 2016-06-06 | 2018-06-05 | 南京航空航天大学 | Flexible radiation protection material with radiation warning and temp regulating function and preparation method thereof |
| CN114149740A (en) * | 2021-11-30 | 2022-03-08 | 北京卫星制造厂有限公司 | Radiation protection coating and preparation method thereof |
| 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 |
| CN117810207A (en) * | 2023-12-29 | 2024-04-02 | 深圳市安信达存储技术有限公司 | Metal sheet packaging method of embedded memory chip in space environment satellite |
| CN117810207B (en) * | 2023-12-29 | 2024-07-26 | 深圳市安信达存储技术有限公司 | Metal sheet packaging method of embedded memory chip in space environment satellite |
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