抄録
The experiments in which water as propellant is heated and ejected from the nozzle of the solar thermal thruster has been conducted. Thermal analysis of the solar thermal thruster and the propellant has been conducted These results indicate that the highest performance is achieved at a largest mass flow rate for a heat input, where propellant finish boiling at the entrance of the nozzle. Analytical result has indicated that the temperature distribution of the thruster was not ideal for heating propellant because of the heat lost at a nozzle. This is the problem to try to improve propulsive performance. It is possible that this problem is solved by using plug nozzle as a nozzle.
