Pure Appl. Chem., 2008, Vol. 80, No. 9, pp. 2013-2023
doi:10.1351/pac200880092013
Microplasma thruster for ultra-small satellites: Plasma chemical and aerodynamical aspects
Abstract:
A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm in diameter and ~10 mm long, being operated at around atmospheric pressures; the micronozzle was a converging-diverging type, having a throat ~0.2 mm in diameter and ~1 mm long. Numerical and experimental results with Ar as a working gas demonstrated that this miniature electrothermal thruster gives a thrust of >1 mN, a specific impulse of ~100 s, and a thrust efficiency of ~10 % at a microwave power of <10 W, making it applicable to attitude-control and station-keeping maneuver for a microspacecraft of <10 kg.
Keywords
electric propulsion; microdischarge; micronozzle flow; microplasma; microplasma jets; micropropulsion; microthrusters; nano- and pico-satellites; plasma thrusters; surface wave-excited plasma.
Conference
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