"Energetic ionic liquids capable of dual-mode chemical monopropellant or bipropellant and electric electrospray rocket propulsion are investigated. Following an extensive literature review, ionic liquids [Bmim][dca], [Bmim][NO₃], and [Emim][EtSO₄] are selected for study since their physical properties align well with the current state-of-the-art in chemical and electrospray propellants. Simulations show that these liquids will not be useful for monopropellant propulsion due to the prediction of solid carbon formation in the exhaust and performance 13-23% below that of hydrazine. Considering these ionic liquids as a fuel component in a binary monopropellant mixture with hydroxyl ammonium nitrate shows 1-4% improved specific impulse over some 'green' monopropellants, while avoiding volatility issues and reducing the number of electrospray emitters by 18-27% and power required by 9-16%, with oxidizing ionic liquid fuels providing the greatest savings.
Mixtures of HAN with ionic liquid fuels [Bmim][NO₃] and [Emim][EtSO₄] are synthesized and tested for catalytic decomposition in a micro-reactor to investigate their potential for use as monopropellants. Two unsupported catalyst materials were tested with the novel propellants: rhenium and iridium. For the [Bmim][NO₃]/HAN propellant, 30 µL droplets on rhenium preheated to 160⁰C yielded a pressure rise rate of 26 mbar/s, compared to 14 mbar/s for iridium and 12 mbar/s for no catalyst. [Emim][EtSO₄]/HAN propellant shows slightly less activity at 160⁰C preheat temperature, yielding a pressure rise rate of 20 mbar/s, 4 mbar/s, and 2.5 mbar/s for injection onto rhenium, iridium, and the thermal plate, respectively"--Abstract, page iv.
Rovey, Joshua L.
Riggins, David W.
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
Missouri Space Grant Consortium
Missouri University of Science and Technology
Journal article titles appearing in thesis/dissertation
- Assessment of imidazole-based ionic liquids as dual-mode spacecraft propellants
- Decomposition of monopropellant blends of HAN and imidazole-based ionic liquid fuels
xi, 91 pages
© 2012 Steven Paul Berg, All rights reserved.
Thesis - Open Access
Library of Congress Subject Headings
Rockets (Aeronautics) -- Fuel
Space vehicles -- Propulsion systems
Print OCLC #
Electronic OCLC #
Link to Catalog Recordhttp://laurel.lso.missouri.edu/record=b9388737~S5
Berg, Steven Paul, "Design and development of ionic liquid dual-mode spacecraft propellants" (2012). Masters Theses. 5149.