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Radiation shielding estimates for manned Mars space flightIn 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.
Document ID
20040090399
Acquisition Source
Johnson Space Center
Document Type
Reprint (Version printed in journal)
Authors
Dudkin, V. E.
(Research Centre of Radiation Protection in the Cosmos Moscow, U.S.S.R)
Kovalev, E. E.
Kolomensky, A. V.
Sakovich, V. A.
Semenov, V. F.
Demin, V. P.
Benton, E. V.
Date Acquired
August 21, 2013
Publication Date
January 1, 1992
Publication Information
Publication: International Journal Of Radiation Applications And Instrumentation. Part D, Nuclear Tracks And Radiation Measurements
Volume: 20
Issue: 1
ISSN: 0735-245X
Subject Category
Lunar And Planetary Science And Exploration
Funding Number(s)
CONTRACT_GRANT: NAG9-235
CONTRACT_GRANT: NCC2-521
Distribution Limits
Public
Copyright
Other
Keywords
Non-NASA Center
NASA Program Flight
NASA Program Radiation Health
NASA Discipline Number 04-10
NASA Discipline Number 00-00
NASA Discipline Radiation Health

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