Analysis of triple langmuir probe measurements in the near-exit region of a gas-fed pulsed plasma thruster

Michael Gagne, Nikos A. Gatsonis, John Blandino, John K. Ziemer, Edgar Yazid Choueiri

Research output: Contribution to conferencePaper

1 Scopus citations

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 languageEnglish (US)
StatePublished - Jan 1 1999
Event35th Joint Propulsion Conference and Exhibit, 1999 - Los Angeles, United States
Duration: Jun 20 1999Jun 24 1999

Other

Other35th Joint Propulsion Conference and Exhibit, 1999
CountryUnited States
CityLos Angeles
Period6/20/996/24/99

All Science Journal Classification (ASJC) codes

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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  • Cite this

    Gagne, M., Gatsonis, N. A., Blandino, J., Ziemer, J. K., & Choueiri, E. Y. (1999). Analysis of triple langmuir probe measurements in the near-exit region of a gas-fed pulsed plasma thruster. Paper presented at 35th Joint Propulsion Conference and Exhibit, 1999, Los Angeles, United States.