Energy deposition in low-power coaxial plasma thrusters
- NASA, Lewis Research Center (United States) Sverdrup Technology, Inc., Cleveland, OH (United States) Princeton University, NJ (United States)
An experimental examination of energy deposition in self-field, coaxial plasma thrusters revealed that the thrust efficiency ranged from 2-9 percent and that the dominant losses resulted from electrode heating and propellant ionization. Sensible enthalpy and radiative losses were negligible. Thruster specific impulse increased with current, ranging from 550-1750 seconds. Spectroscopic studies of the plume plasma showed that the electron temperature ranged from 0.5-2.5 eV and that the dominant species were singly and doubly ionized argon. Attempts to raise thruster efficiency by increasing the chamber pressure resulted in reduced electrode losses and lowered I(sp), but the thrust efficiency decreased because of a current redistribution that lowered the thrust beyond expectations. 25 refs.
- OSTI ID:
- 6006514
- Journal Information:
- Journal of Propulsion and Power; (United States), Journal Name: Journal of Propulsion and Power; (United States) Vol. 7; ISSN JPPOE; ISSN 0748-4658
- Country of Publication:
- United States
- Language:
- English
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