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چکیده
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The damages and logical failures in di erent parts of a satellite may occur during asolar event, when a bulk of solar energetic particles approaching the Earth. Duringsolar events, these particles may cause extensive damages which are even permanent(hard errors). A way of damage reduction is designing a proper coating as the fuselage.As protons are the major component of solar particles and because the most of harderrors are caused by neutrons, in this work, we evaluated di erent shielding materialagainst these type of errors. To avoid hard errors due to neutrons, we need to knowsolar energetic particles ux. During a solar are a satellite receives the maximum uxof protons, so we used protons with an energy range of 100MeVto 1GeVwhich isthe most sensitive energy range to the Sun activities. In the present work, we havecalculated the ux of solar energetic particles which collides a typical satellite in lowearth orbit. Using OMERE software, coordinates and speci cations of a satellite weredetermined virtually and this typical satellite were used to calculate the typical valuesof particles uxes received by satellite during di erent solar ares of di erent solarcycles during occurrence of solar ares. Then, we have used FLUKA software, to study10 di erent material layers as typical fuselages assuming proton primaries collide withthem in the above energy ranges. Then we calculated neutron uxes produced whena proton interacts with these materials. At the nal stage we have shown that in thisenergy ranges Aluminum makes the best shielding against solar particles and addingMagnesium to alloy may improve the fuselage protection against hard errors.
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