Radiation shielding estimates for manned Mars space flight
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...
| Veröffentlicht in: | International Journal Of Radiation Applications And Instrumentation. Part D, Nuclear Tracks And Radiation Measurements. - 1990. - 20(1992), 1 vom: 07. Jan., Seite 29-32 |
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| 1. Verfasser: | |
| Weitere Verfasser: | , , , , , |
| Format: | Aufsatz |
| Sprache: | English |
| Veröffentlicht: |
1992
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| Zugriff auf das übergeordnete Werk: | International Journal Of Radiation Applications And Instrumentation. Part D, Nuclear Tracks And Radiation Measurements |
| Schlagworte: | Journal Article Research Support, U.S. Gov't, Non-P.H.S. Research Support, U.S. Gov't, P.H.S. NASA Discipline Number 00-00 NASA Discipline Number 04-10 NASA Discipline Radiation Health NASA Program Flight NASA Program Radiation Health Non-NASA Center |
| Zusammenfassung: | 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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| Beschreibung: | Date Completed 10.05.1995 Date Revised 05.11.2019 published: Print Citation Status MEDLINE |
| ISSN: | 0735-245X |