Abstract
Triple Langmuir probes were used to measure electron number density, and electron temperature in the near-exit region of a laboratory model gas-fed pulsed plasma thruster. Triple Langmuir probe data was obtained on a plane parallel to the thruster electrodes at radial distances of 3 and 7 cm downstream of the propellant inlet and angular positions of 0, 10,20, and 30 degrees. The thruster was operated with Xe propellant, 2 J per pulse, and a mass flow rate of 3 mg/s. Analysis shows that average density at the thruster exit plane is in the range of 5xl018 to 2.5×1019 m-3 and temperature is in the range of 0.5 to 4 eV. At a radial distance of 4 cm downstream from the exit, the density is in the range of 2×1018 to 1×1019 m-3 and temperature in the range of 0.2 to 1.4 eV. Temperature averaged over the duration of a pulse is in the range of 0.4 to 1.3 eV and shows angular and radial variation.
Original language | English (US) |
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State | Published - 1999 |
Event | 35th Joint Propulsion Conference and Exhibit, 1999 - Los Angeles, United States Duration: Jun 20 1999 → Jun 24 1999 |
Other
Other | 35th Joint Propulsion Conference and Exhibit, 1999 |
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Country/Territory | United States |
City | Los Angeles |
Period | 6/20/99 → 6/24/99 |
All Science Journal Classification (ASJC) codes
- Energy Engineering and Power Technology
- Electrical and Electronic Engineering
- Mechanical Engineering
- Control and Systems Engineering
- Aerospace Engineering