CN103832599A - Composite shielding method for satellite to resist total dose effect - Google Patents
Composite shielding method for satellite to resist total dose effect Download PDFInfo
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- CN103832599A CN103832599A CN201210490975.8A CN201210490975A CN103832599A CN 103832599 A CN103832599 A CN 103832599A CN 201210490975 A CN201210490975 A CN 201210490975A CN 103832599 A CN103832599 A CN 103832599A
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Abstract
The invention provides a composite shielding method for a satellite to resist a total dose effect. The composite shielding method for the satellite to resist the total dose effect is characterized in that according to the method, double-layer materials are used for shielding, metal with the low atomic number is used for an outer layer, and metal with the high atomic number is used for an inner layer. The metal with the low atomic number is aluminium, and the metal with the high atomic number is tantalum. According to the composite shielding method, the mass ratio of the metal aluminium and the metal tantalum is determined according to the specific orbit environment where the satellite is placed. According to the technical scheme, under the condition that the same shielding effect as a traditional method is achieved, the total quantity of the used shielding materials is smaller; or under the condition of the same shielding quality, a better shielding effect can be achieved.
Description
Technical field
The present invention relates to a kind of anti-radiation shield method, is mainly the shielding to the suffered total dose of electronics package on satellite, the invention provides a kind of composite shielding method for resistant to total dose effect on satellite.
Background technology
Satellite orbits and is faced with severe space radiation environment, comprise solar proton, radiation belts of the Earth and galactic cosmic ray etc., the above two are the main particle sources of causing total dose effect, these high energy charged particles incident satellite electron devices, make device material ionization produce total dose effect, the performance of electronics package is caused and had a strong impact on.Conventionally its total dose suffering of satellite about several years time in orbit has substantially exceeded the level of general electronics package resistant to total dose, and therefore radiation-resistant work is very necessary.
The means of defence of total dose mainly contains two kinds: 1) microelectronics radiation hardening technology, by microelectronic material choose, the measure such as microcircuit design, technological design, topology layout reduces the impact of total dose on parameters of electronic device; 2) adopt exterior material to shield device.
Method proposed by the invention belongs to the second.Common shielding material is to adopt simple aluminium, and effect is often unsatisfactory, and for reaching the shield effectiveness of expection, needs the aluminum that thickness is larger to shield, and has wasted the limited quality resource of satellite.
Summary of the invention
The object of the invention is to, for overcoming the problems referred to above, the invention provides the composite shielding method of resistant to total dose effect on a kind of satellite.
For achieving the above object, the invention provides a kind of composite shielding method for resistant to total dose effect on satellite, it is characterized in that, described method is: adopt double layer material to shield, outer adopt the metal of low atomic number and internal layer adopts the metal of high atomic number.
The metal of above-mentioned low atomic number is aluminium, and the metal of high atomic number is tantalum.
Compared with prior art, technical advantage of the present invention is:
In the case of reaching the shield effectiveness identical with orthodox method, the shielding material total mass of the double layer material that adopts is less; And the in the situation that of same screening mass, can reach better shield effectiveness.
Accompanying drawing explanation
Fig. 1-a and 1-b are the dosage of certain electron spectrum after different equivalent thickness and different component shielding material;
Fig. 2 is the Contrast on effect of the shielding of traditional fine aluminium and pure tantalum screen and composite shielding.
The specific embodiment
Below in conjunction with accompanying drawing, content of the present invention is described in detail.
Adopt double layer material to shield in order to reduce the quality of shielding material under the prerequisite reaching expection shield effectiveness, to the present invention proposes, concrete scheme is the outer metal (as aluminium) that adopts low atomic number, and internal layer adopts the metal (as tantalum) of high atomic number.
From nuclear physics correlation theory, the material actv. scattered electron more that atomic number (Z) is high, but the stopping power of low Z materials unit mass is lower, and produce more bremsstrahlung (bremsstrahlung coefficient is directly proportional to atomic number and the incident electron energy of material), if and pass through again low Z materials after first allowing electronics underspeed by high Z materials, can effectively reduce by high Z materials like this energy of electronics, the bremsstrahlung producing in low Z materials thus reduces, and in this way the electron dose after shielding can significantly reduce.Therefore main problem is exactly will solve in the situation that shielding material equivalent thickness is constant, and high atomic number material and low atomic number material can obtain optimum shield effectiveness with which kind of ratio combination.
The present invention, in conjunction with the space environment feature of typical satellite orbit, regulates the thickness of two-layer screen layer, filters out optimum factors for radiation shielding design under the condition that takies minimum quality resource.
Concrete thinking is, choose respectively metallic aluminium and tantalum as low Z and high Z metal composition double layer screen material, allow particle pass through after shielding, record the total dose that particle produces in detector, under the constant condition of shielding material equivalent thickness, make the percent by weight of aluminium be increased to 100% from 0%, obtain the curve that a total dose changes with the percent by weight of aluminium, and then change shielding material equivalent thickness, make many such curves, can draw optimum assembly in different equivalent thickness situation (being the percentum of hour aluminium of dosage) by analyzing.According to the concrete orbital environment at satellite place, metallic aluminium accounts for the 20%-40% of total screening mass.
Embodiment mono-:
Make analogue computing as an example of the electron spectrum of certain track example, the equivalent thickness of aluminium of shielding material from 2 millimeters, 2.5 millimeters to 20 millimeters not etc., the mass ratio that wherein every kind of equivalent thickness of aluminium is got respectively aluminium be 0%, 5% to 100% totally 12 kinds of combinations carry out analogue computing.
Result of calculation as shown in Fig. 1-a and 1-b, the percent by weight that wherein abscissa is aluminium, ordinate be shielding after relative total dose, different curves represent different equivalent thickness of aluminiums.As seen from the figure, compare with traditional fine aluminium shielding, adopt composite shielding post dose to reduce a lot, while being 2.5mm such as equivalent thickness of aluminium, the composite shielding effect of 10% aluminium is best; If increase equivalent thickness, dosage nadir can move to the heavy larger side of aluminum ratio, and during such as 3.0mm, nadir is 15%, and nadir is 25% during to 5.5mm.
Fig. 2 be fine aluminium and pure tantalum to the depth curve of electron spectrum with carry out the contrast after composite shielding optimal design, visible composite shielding can effectively reduce total dose, and the larger effect of equivalent thickness is more obvious.Such as the 3mm equivalent thickness of aluminium in the situation that, the shield effectiveness of this composite shielding method is 4 times of left and right of common fine aluminium.
It should be noted last that, above embodiment is only unrestricted in order to technical scheme of the present invention to be described.Although the present invention is had been described in detail with reference to embodiment, those of ordinary skill in the art is to be understood that, technical scheme of the present invention is modified or is equal to replacement, do not depart from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of claim scope of the present invention.
Claims (4)
1. for a composite shielding method for resistant to total dose effect on satellite, it is characterized in that, described method is:
Adopt double layer material to shield, outer adopt the metal of low atomic number and internal layer adopts the metal of high atomic number.
2. the composite shielding method for resistant to total dose effect on satellite according to claim 1, is characterized in that, the metal of described low atomic number is aluminium.
3. the composite shielding method for resistant to total dose effect on satellite according to claim 1 and 2, is characterized in that, the metal of described high atomic number is tantalum.
4. the composite shielding method for resistant to total dose effect on satellite according to claim 3, is characterized in that, described metallic aluminium accounts for the 20%-40% of total screening mass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201210490975.8A CN103832599A (en) | 2012-11-27 | 2012-11-27 | Composite shielding method for satellite to resist total dose effect |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210490975.8A CN103832599A (en) | 2012-11-27 | 2012-11-27 | Composite shielding method for satellite to resist total dose effect |
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| CN103832599A true CN103832599A (en) | 2014-06-04 |
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| CN201210490975.8A Pending CN103832599A (en) | 2012-11-27 | 2012-11-27 | Composite shielding method for satellite to resist total dose effect |
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Cited By (2)
| 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 |
| CN113543615A (en) * | 2021-06-29 | 2021-10-22 | 中国科学院长春光学精密机械与物理研究所 | Irradiation protection method for space electronic equipment |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2151704A1 (en) * | 2008-08-07 | 2010-02-10 | Thales Alenia Space Italia S.p.A. | Shielding device for optical and/or electronic apparatuses, and space vehicle comprising such device |
| CN102490913A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Anti-total-dose shielding device |
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2012
- 2012-11-27 CN CN201210490975.8A patent/CN103832599A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2151704A1 (en) * | 2008-08-07 | 2010-02-10 | Thales Alenia Space Italia S.p.A. | Shielding device for optical and/or electronic apparatuses, and space vehicle comprising such device |
| CN102490913A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Anti-total-dose shielding device |
Non-Patent Citations (1)
| Title |
|---|
| 杨晓军等: "金属/聚合物复合材料对中能电子的屏蔽作用研究", 《核技术》, vol. 29, no. 11, 10 November 2006 (2006-11-10), pages 817 - 820 * |
Cited By (3)
| 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 |
| CN113543615A (en) * | 2021-06-29 | 2021-10-22 | 中国科学院长春光学精密机械与物理研究所 | Irradiation protection method for space electronic equipment |
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Application publication date: 20140604 |