Thrust and Performance Study of Micro Pulsed Plasma Thrusters

Abstract

This research is focused on several areas of the micro PPT performance. An important idea studied is the effect of lifetime use on the performance. The thruster is fired for a simulated lifetime of use to see if there is an impact on the thrust of the thruster later in life. Also vital is the efficiency of the thruster. A micro PPT performing at max efficiency will ionize all ablated material; however, we know that not to be the case. In this research the effort is made to collect these non-ionized particles in order to measure their mass post-test. With this collected mass and a knowledge of how much the thruster has ablated, it can be determined what percentage of the propellant has been ionized. With the non-ionized particles also comes a concern about contamination. Knowing the amount of particles that can collect at the end of a lifetime of use allows a better understanding of what contamination issues a spacecraft may have and what precautions need to be made.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2010
Accession Number
ADA516751

Entities

People

  • Jeremy J. Selstrom

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Electric Propulsion
  • Electromagnetic Fields
  • Hall Thrusters
  • Magnetic Fields
  • Materials
  • Measurement
  • Propulsion Systems
  • Pulsed Plasma Thrusters
  • Rate Of Consumption
  • Small Satellites
  • Spacecraft
  • Test Equipment
  • Thrust
  • Thrusters
  • Voltage

Readers

  • Aerospace Propulsion Engineering.
  • Pulsed Power and Plasma Physics.
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Hall-Effect Thruster