Due to the movable injector which can be regarded as a differential piston with some spray holes

the pulse thruster can provide much higher chamber pressure than the supply pressure of propellant.In order to analyze the operating characteristics of this type of pulse thruster adopting the monopropellant of HAN(hydroxylammonium nitrate)

a lumped parameter model was established and the fourth-order Runge-Kutta method was applied to get its numerical solution which reflected the unique pulsating characteristics.The influence of the structural parameters on the thruster performance such as the area of injection holes

nozzle throat area

displacement and differential area ratio of the movable injector was analyzed and summarized.Though the pulsating operation would come to change when any of the above parameters is altered

the displacement and the nozzle throat area are the most influential and should be optimized firstly in the design progress of the new type of pulse thruster.The average pressure in the combustion chamber and the average specific impulse of the thruster are sensitive to the injector displacement

and the average thrust is sensitive to the nozzle throat area.