Propellant Inefficiency Due to Particulates in a Pulsed Plasma Thruster

Abstract

Propellant inefficiency resulting from the ejection of propellant material in particulate form is characterized in a Pulsed Plasma Thruster (PPT). Exhaust deposits are collected and analyzed using a combination of Scanning Electron Microscope (SEM), Energy Dispersive X-ray Analysis. (EDAX), and microscopic imaging. Teflon particulates are observed with sizes ranging from over 100 mum down to less than 1 mum. Estimates of the mass entrained in this form show that the particulates may account for up to 30% of the total propellant mass used, indicating that methods of ameliorating this loss mechanism would result in significant improvements in the PPT thrust efficiency.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1997
Accession Number
ADA437494

Entities

People

  • Gregory G. Spanjers
  • Jason S. Lotspeich
  • Keith A. Mcfall
  • Ronald A. Spores

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Efficiency
  • Electron Microscopes
  • Electron Microscopy
  • Energy
  • Materials
  • Measurement
  • Mechanical Engineering
  • Microscopes
  • Microscopy
  • Particle Size
  • Particles
  • Propellants
  • Pulsed Plasma Thrusters
  • Spatial Distribution
  • Spectra
  • X Rays

Fields of Study

  • Physics

Readers

  • Aerosol Science/Aerosol Physics
  • Aerospace Propulsion Engineering.
  • Thin Film Deposition Science.

Technology Areas

  • Microelectronics
  • Space
  • Space - Hall-Effect Thruster