Linear burn rate of ionic liquid multimode monopropellant

Nicolas Rasmont, Emil J. Broemmelsiek, Alex J. Mundahl, Joshua L. Rovey

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

Abstract

Multimode microthrusters are capable of both high specific impulse electrical operation and high thrust chemical operation, allowing a high degree of mission flexibility for small satellites. This technology requires a monopropellant capable of sustaining both modes of propulsion, through catalytic exothermic decomposition (chemical mode) and electrospray (electric mode). Previous research has identified a double-salt ionic liquid consisting of 41% wt. 1-ethyl-3-methylimidazolium ethyl sulfate and 59% wt. hydroxylammonium nitrate as a promising propellant candidate. The objective of this work is to measure its linear burn rate. The burn rate is measured through pressure-based and high-speed imaging methods in a fixed-volume pressurized reactor across a pressure range from 0.5 to 10 MPa. Its performance is compared to benchmarks 80% wt. hydroxylammonium nitrate-water and nitromethane propellants, both of which show good agreement with the literature. The burn rate of the multimode monopropellant is found to follow an exponential law eb = 5. 35e1.11P between 0.5 and 3 MPa and being approximately constant at 140 mm/s between 3 and 10 MPa.

Original languageEnglish (US)
Title of host publicationAIAA Propulsion and Energy Forum and Exposition, 2019
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105906
DOIs
StatePublished - 2019
EventAIAA Propulsion and Energy Forum and Exposition, 2019 - Indianapolis, United States
Duration: Aug 19 2019Aug 22 2019

Publication series

NameAIAA Propulsion and Energy Forum and Exposition, 2019

Conference

ConferenceAIAA Propulsion and Energy Forum and Exposition, 2019
CountryUnited States
CityIndianapolis
Period8/19/198/22/19

ASJC Scopus subject areas

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

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  • Cite this

    Rasmont, N., Broemmelsiek, E. J., Mundahl, A. J., & Rovey, J. L. (2019). Linear burn rate of ionic liquid multimode monopropellant. In AIAA Propulsion and Energy Forum and Exposition, 2019 (AIAA Propulsion and Energy Forum and Exposition, 2019). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-4294