NASA NTRS · 20040090399
Radiation shielding estimates for manned Mars space flight
Abstract
In the analysis of the required radiation shielding protection of spacecraft during a Mars flight, specific effects of solar activity (SA) on the intensity of galactic and solar cosmic rays were taken into consideration. Three spaceflight periods were considered: (1) maximum SA; (2) minimum SA; and (3) intermediate SA, when intensities of both galactic and solar cosmic rays are moderately high. Scenarios of spaceflights utilizing liquid-propellant rocket engines, low- and intermediate-thrust nuclear electrojet engines, and nuclear rocket engines, all of which have been designed in the Soviet Union, are reviewed. Calculations were performed on the basis of a set of standards for radiation protection approved by the U.S.S.R. State Committee for Standards. It was found that the lowest estimated mass of a Mars spacecraft, including the radiation shielding mass, obtained using a combination of a liquid propellant engine with low and intermediate thrust nuclear electrojet engines, would be 500-550 metric tons.
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Dudkin, V. E., Kovalev, E. E., Kolomensky, A. V., Sakovich, V. A., Semenov, V. F., Demin, V. P., Benton, E. V.. 1992-01-01. Radiation shielding estimates for manned Mars space flight. https://ntrs.nasa.gov/citations/20040090399
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