Pulsed Plasma Thrusters (PPT) using Teflon as solid propellant has characteristics of simplicity, lightweight, and high durability in recent years. Therefore, PPT propulsion system has the advantages for the small, micro-and nano-satellite attitude control. Tokyo Metropolitan Institute of Technology (TMIT) has started R & D on PPT system with the collaboration of NASDA. This paper describes its present status of the R & D. In the BBM phase, we tested that hood angle and electrode material was changed. In this result, we have researched optimum performance of TMIT-PPT. Now we have shifted from BBM-phase to EM-phase.
