Eun-Seok Lee , Keun-Shik Chang, Chul Park
International Journal of Aeronautical and Space Sicences, vol. 5, no. 2, pp.54-61, 2004

Abstract : In this paper we carried out a design study for an unmanned Mars mission suitable for Republic of Korea. The mission will use a KSLV series launch system, which is to place a one tonne payload into the LEO. We calculated the velocity incrementst(ΔV) required for departure from Earth and insertion into the orbit around Mars based on the mission opportunity data provided by NASA. Two types of Mars modules - entry type and orbiter type - were considered in this study. We calculated the mass of TPS(thermal protection system) for the entry type Mars module based on the heat transfer rate and heat load from the Mars atmosphere to the surface of the TPS. The heat transfer rate and heat load were obtained through an entry trajectory calculation. For the orbiter type Mars module, we calculated the mass breakdown of the additional spacecraft which is to insert the Mars module into the orbit around Mars. Other mass items were determined by proportioning from the existing Mars modules. This paper finally proposes the payload capacities for each types of Mars modules.

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