One-dimensional model of a pulsed plasma thruster

Abstract

This paper presents a modified one dimensional model for the pulsed plasma thruster. The model takes into account the impact of thruster geometry and capacitor initial energy on plasma inductance and resistance, as well as the ablated mass per pulse. These three factors have significant impact on the performance of the thruster and have not been considered concurrently before. The model is verified by comparing the estimated specific impulse, impulse bit and thrust-to-power ratio with experimental measurements for space qualified thrusters. The maximum error is estimated to be about 8% when using the modified model, while the conventional snowplow model produces error up to about 70%. The modified model is then employed to generate design charts that would help in selecting the proper combination of thruster geometry and energy level in the preliminary design phase of a pulsed plasma thruster for different space missions.

Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster

“…However, conventional slug and snowplow models assume complete ionization of propellant gas and leads to an significant error in predicting the performance of PPTs. In fact, the conventional slug models produced an error up-to 70% in predicting the performance for LES-6 PPT [16]. Slug and snowplow models have been modified to give greater accuracy by accounting the effects of post-pulse macro particle production and gas-dynamic thrust developments [17].…”

Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster

“…However, conventional slug and snowplow models assume complete ionization of propellant gas and leads to an significant error in predicting the performance of PPTs. In fact the conventional slug models produce an error up-to 70% in predicting the performance for LES-6 PPT [16]. Slug and snowplow models 72 have been modified to give greater accuracy by accounting for effects of post-pulse macro particle production and gas-dynamic thrust developments [17].…”