Parametric Study of Auto-Initiated Solid Propellant Pulsed Plasma Micro Thruster

Abstract

*† The present study focuses on understanding the effect of variation in the performance parameters. It includes characterizing the Auto-Initiated Pulsed Plasma Thruster (AI-PPT) with the change in various operational and geometric parameters. The conventional pulsed plasma thrusters have igniter plug as an essential component which is a life limiting factor for the functioning of PPT, as the igniter tip suffers from continuous erosion during operation and also leads to non-uniformity of the current sheet in its proximity. The AI-PPT works without an igniter plug distinct to the conventional PPT’s. This study will be supportive in obtaining optimum performance parameters. The experimental effort is supported by a theoretical model considered during analysis. The study was confined to lower capacitor energies in the range applicable to thrusters used for attitude control of satellites. Both the conventional parallel-rail and later coaxial geometries were tested. The performance parameters at various pressures show that this type of PPT can be employed in the atmospheric pressure range with some modifications in the PPT, like increasing the area of the propellant for increasing the thrust. Analytical and experimental calculations indicate a significant broadening of obtainable range of impulse bit and thrust for a given input, when this PPT has been used. The thruster operation and performance was investigated using discharge characteristics like the current and voltage measurements.