Microwave electrothermal thruster using simulated hydrazine

Daniel E. Clemens, Michael M. Micci, Sven G. Bilén

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

1 Scopus citations


Research was initiated to examine the feasibility of operating the microwave electrothermal thruster (MET) using the products of hydrazine decomposition as the propellant gas. Testing was conducted on the low-power (∼100 W) 7.5-GHz MET in vacuum using various mixtures of N2, H2, and NH3 to simulate decomposed hydrazine in an effort to determine the performance effects of variation of nozzle throat diameter, microwave frequency, and microwave power. Thrust and specific impulse measurements were also obtained. Using a cold N2 + 2H2 propellant mixture, a specific impulse of 140 s was measured. Results are encouraging for further development of the MET for operation with hydrazine.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Number of pages14
StatePublished - 2006
EventAIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference - Sacramento, CA, United States
Duration: Jul 9 2006Jul 12 2006

Publication series

NameCollection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference


OtherAIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Country/TerritoryUnited States
CitySacramento, CA

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Energy(all)
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering


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