Abstract
In this study, liquid propellant-pulsed plasma thruster (LP-PPT) is proposed in order to develop a microthruster. A pulsed plasma thruster (PPT) is a promising microthruster since it is very compact, light, and robust. On the other hand, the conventional PPT has the following problems: contamination, low thrust performance and non-uniform propellant consumption. In order to solve these problems, liquid is used as a propellant. Using water or alcohol as a propellant, PPT plume would be clean. Moreover, all liquid propellant would be available by using the liquid injector. With a designed thruster and a designed injector, injecting the required amount of liquid (10 μg order) and the LP-PPT operation were demonstrated. An impulse bit was measured with a designed torsional thrust stand with a resolution of 1 μN s. Thrust measurement yielded a specific impulse of 4300 s and a thrust efficiency of 13% with a capacitor-stored energy of 20 J. This thruster performance is comparable to that of the conventional PPT.
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