Accession Number : ADA325644

Title :   Particulate Emission from a Pulsed Plasma Thruster.

Descriptive Note : Technical paper,

Corporate Author : PHILLIPS LAB EDWARDS AFB CA

Personal Author(s) : Spanjers, Gregory G. ; Lopspeich, Jason S. ; McFall, Keith A. ; Spores, Ronald A.

Report Date : DEC 1996

Pagination or Media Count : 8

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 microns down to less than 1 microns. Estimates of the mass entrained in this form show that the particulates may account for up to 20% of the total propellant mass used, indicating that methods of ameliorating this loss mechanism would result in significant improvements in the PPT thrust efficiency.

Descriptors :   *THRUSTERS, *PLASMA ENGINES, INTEGRATED SYSTEMS, PLASMAS(PHYSICS), ARTIFICIAL SATELLITES, PARTICULATES, SOLID ROCKET PROPELLANTS, ROCKET EXHAUST, TETRAFLUOROETHYLENE RESINS, SPACE PROPULSION, THRUST AUGMENTATION.

Subject Categories : Electric and Ion Propulsion
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE