电邮这篇文章 Оценка ожидаемых доз радиации при перелете к Луне с использованием двигателей малой тяги
- 作者: Турундаевский А.Н.1, Николаева Н.И.1, Панов А.Д.1, Подзолко М.В.1, Подорожный Д.М.1, Рахимчанова К.Р.1
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隶属关系:
- Московский государственный университет имени М. В. Ломоносова
- 期: 卷 62, 编号 4 (2024)
- 页面: 385-388
- 栏目: Articles
- URL: https://rjmseer.com/0023-4206/article/view/672380
- DOI: https://doi.org/10.31857/S0023420624040081
- EDN: https://elibrary.ru/JIRENO
- ID: 672380
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Fig. 1. Daily radiation dose as a function of orbital radius: 1 – for a shielding thickness of 0.01 g/cm2; 2 – for 1 g/cm2. Dashed line – ERB contribution; thin solid line – SCR contribution; thick solid line – absorbed dose from all components (ERB, SCR, GCR). Above – graphs for solar minimum, below – for maximum. The GCR contribution is not shown separately (it is very small), but is taken into account when calculating the total dose.
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Fig. 2. Accumulated absorbed radiation dose as a function of flight time for an engine thrust of 6.5 N: 1 – for a shielding thickness of 0.01 g/cm2; 2 – for 1 g/cm2. Thin solid line – SCR contribution; thick solid line – absorbed dose from all components (ERB, SCR, GCR). Above – graphs for solar minimum; below – for the maximum. The contribution of the RPS in this scale merges with the line of the total absorbed dose. The contribution of the GCR is not shown separately (it is very small), but is taken into account when calculating the total absorbed dose.
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Fig. 3. The same as in Fig. 2, but with an engine thrust of 13 N.
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Fig. 4. Dependence of the total absorbed doses of radiation (for the entire flight) on the thickness of the shielding. The thick line is a thrust of 6.5 N, the thin line is a thrust of 13 N. On the left are graphs for the solar minimum, on the right – for the maximum.
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