Plasma plume characterization of electric solid propellant pulsed microthrusters

Matthew S. Glascock, Joshua L. Rovey, Shae Williams, Jason Thrasher

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Electric Solid Propellants are an exciting potential option for propulsion because they are ignited only by an applied electric current. This leads to exciting capabilities such as on-demand throttling and re-ignition, and insensitivity to accidental ignition by spark, impact or open flame. Digital Solid State Propulsion has developed a pulsed microthruster using an electric solid propellant. In this work, the plasma plume created by these microthrusters is investigated using a nude Faraday Probe, an array of single Langmuir Probes, a triple Langmuir probe and Residual Gas Analysis. The thruster was tested at a vacuum level of 2×10-5 Torr. Results indicate a peak centerline ion current density of about 200 mA/cm2, peak electron temperature of about 1 eV and peak electron density of between 1 and 2×1011 cm-3. Additionally, ionization fraction estimates are < 1% of an ablation mass bit of about 250 µg on average. Exhaust velocity estimates are largely inconclusive, but are on the order of a few km/s.

Original languageEnglish (US)
Title of host publication51st AIAA/SAE/ASEE Joint Propulsion Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103216
StatePublished - 2015
Externally publishedYes
Event51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015 - Orlando, United States
Duration: Jul 27 2015Jul 29 2015

Publication series

Name51st AIAA/SAE/ASEE Joint Propulsion Conference

Other

Other51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015
Country/TerritoryUnited States
CityOrlando
Period7/27/157/29/15

ASJC Scopus subject areas

  • Engineering(all)

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