It has been known by past explorations that metal and water (H_2O) exists on the moon and Mars. And H_2O is expected as an oxidizer of the in-situ solid propellant. To use H_2O as oxidizer, the high temperature metal which reacts readily with H_2O is needed. Terefore, we selected Magnesium (Mg)/Teflon/PEO/H_2O as sample propellant In this study, we obtain the burning rate of the sample propellant, the combustion efficiency of C~*, and the hydorogen gas generation ratio . The maximum combustion efficiency of C~* is 94% obtained at the concentration of H_2O equal 15 parts. The concentration of generated H_2 gas increases with increasing the concentration of H_2O , and the H_2 gas generation ratio is over 82% all of the concentration of H_2O.
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