Performance of pulsed plasma thruster at low discharge energy

Abstract

As the size of satellites are scaling down, low power and compact propulsion systems such as the Pulsed Plasma Thruster (PPT) are needed for stabilizing these miniature satellites in orbit. Most PPT systems have been operated at 2 J or more of discharge energy. In this work, the performance of a PPT with a side-fed, tongue-flared electrode configuration operated at a range of lower discharge energy of 0.5 to 2.5 J has been investigated. Ablation and charring of the Teflon propellant surface were analysed through Field Effect Scanning Electron Microscopy (FESEM) imaging and Energy Dispersive X-Ray (EDX) spectra. It was found that at discharge energy below 2 J, inconsistency in specific impulse and thrust efficiency resulted from the low mass bit measured. At energies more than 2 J, the performance parameters are compared and extensively discussed with other PPT systems of similar configuration.