Study on Specific Mass of Nuclear Electric Propulsion System with Closed Cycle MHD Generator

摘要

In space, radiation dose to crew increases in proportion to a increase of flight-time. High radiation dose to human have an influence on human health. Therefore, propulsion system that can minimize in-flight time is required. In the present study, to minimize in-flight time, nuclear electric propulsion system (NEP system) is suggested for human exploration to Mars. NEP system consists of CCMHD power generation system driven by nuclear fission reactor (NFR) providing electric power to the propulsion system and the variable specific impulse magneto-plasma rocket (VASIMR~?). In this study, modeling of power plant for NEP system and system analysis of it is carried out. Then Parameter are changed, the outlet temperature of NFR, the radiator temperature and the enthalpy extraction of MHD generator, in order to know how to minimize specific mass In the outlet temperature of NFR change, specific mass of NEP system decreases with an increase of outlet temperature of NFR. In the radiator temperature change, specific mass of NEP system have minimum point in radiator temperature. In the enthalpy extraction of MHD generator, specific mass of NEP system have minimum point in enthalpy extraction. Specific mass of NEP system less than α_(system) = 2[kg / kWe] could be expected.