Abstract
Green monopropellant thrusters, such as HAN-based and ADN-based monopropellant thruster, have been continuously developed as replacement for conventional hydrazine thrusters. A green monopropellant reaction system by utilizing discharge plasma of swirling noble gas has been proposed in substitution for the solid catalyst. Objective of this study is to evaluate the thrust performance of HAN-based monopropellant thruster with discharge plasma system by the measurement of combustion chamber pressure under vacuum. As a result, stable operations were confirmed by the measurement of combustion chamber pressure and internal pressure of argon-tube. At argon mass flow rate of 0.13g/s, HAN-based monopropellant mass flow rate of 0.31g/s and nozzle expansion ratio of 1, power consumption, c-star efficiency and rising time of combustion chamber pressure were 484W, 54% and 597ms, respectively. In addition, predicted thrust and specific impulse by the measured combustion chamber pressure were 282mN and 93s, respectively.
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