Development and preliminary testing of an electrolytic ignition microthruster for space propulsion

Ming Hsun Wu, Richard A. Yetter

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

Abstract

A liquid monopropellant microthruster utilizing electrolysis for ignition was designed and fabricated using low temperature co-fired ceramic tape technology. The volume of the thruster combustion chamber was 0.82 mm3. The microthruster had integrated silver electrodes to enable ignition of hydroxylammonium nitrate based liquid monopropellants by electrolytic decomposition. Energy input as small as 1.9 J produced high temperature ignition, and ignition delay times as short as 224.5 ms were achieved. A thrust output of approximately 200 mN was measured with a voltage input of 45 V.

Original languageEnglish (US)
Title of host publicationFall Technical Meeting of the Eastern States Section of the Combustion Institute 2007 "Chemical and Physical Processes in Combustion"
PublisherCombustion Institute
Pages246-249
Number of pages4
ISBN (Electronic)9781604239454
StatePublished - 2007
EventFall Technical Meeting of the Eastern States Section of the Combustion Institute 2007: Chemical and Physical Processes in Combustion - Charlottesville, United States
Duration: Oct 21 2007Oct 24 2007

Publication series

NameFall Technical Meeting of the Eastern States Section of the Combustion Institute 2007 "Chemical and Physical Processes in Combustion"

Other

OtherFall Technical Meeting of the Eastern States Section of the Combustion Institute 2007: Chemical and Physical Processes in Combustion
CountryUnited States
CityCharlottesville
Period10/21/0710/24/07

All Science Journal Classification (ASJC) codes

  • Chemical Engineering(all)
  • Mechanical Engineering
  • Physical and Theoretical Chemistry

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