TY - JOUR
T1 - Linear burn rate of green ionic liquid multimode monopropellant
AU - Rasmont, Nicolas
AU - Broemmelsiek, Emil J.
AU - Rovey, Joshua L.
N1 - Funding Information:
The authors thank the technicians within the department machine shop for their assistance in the manufacturing process of this experiment. This project was supported by the University of Illinois at Urbana-Champaign Grainger College of Engineering.
PY - 2020/9
Y1 - 2020/9
N2 - Multimode space propulsion systems are being proposed that integrate high specific impulse electric propulsion and high thrust chemical propulsion. The most important attribute of this concept is a shared propellant capable of both modes of propulsion, which enables mission flexibility. One promising approach is a catalytic monopropellant thruster paired with an electrospray electric thruster. Previous research has identified a green double-salt ionic liquid consisting of 41% wt. 1-ethyl-3-methylimidazolium ethyl sulfate and 59% wt. hydroxylammonium nitrate as a promising propellant candidate. In this work, the burn rate of this monopropellant is measured through pressure-based and high-speed imaging methods in a fixed-volume chamber pressurized across a pressure range from 0.5 to 10 MPa. Its performance is benchmarked by 80% wt. hydroxylammonium nitrate-water and nitromethane propellants. The burn rate of the multimode monopropellant is found to follow an exponential law given by rb=5.35exp1.11P between 0.5 and 3 MPa and is approximately constant at 142 ± 29 mm/s between 3 and 10 MPa.
AB - Multimode space propulsion systems are being proposed that integrate high specific impulse electric propulsion and high thrust chemical propulsion. The most important attribute of this concept is a shared propellant capable of both modes of propulsion, which enables mission flexibility. One promising approach is a catalytic monopropellant thruster paired with an electrospray electric thruster. Previous research has identified a green double-salt ionic liquid consisting of 41% wt. 1-ethyl-3-methylimidazolium ethyl sulfate and 59% wt. hydroxylammonium nitrate as a promising propellant candidate. In this work, the burn rate of this monopropellant is measured through pressure-based and high-speed imaging methods in a fixed-volume chamber pressurized across a pressure range from 0.5 to 10 MPa. Its performance is benchmarked by 80% wt. hydroxylammonium nitrate-water and nitromethane propellants. The burn rate of the multimode monopropellant is found to follow an exponential law given by rb=5.35exp1.11P between 0.5 and 3 MPa and is approximately constant at 142 ± 29 mm/s between 3 and 10 MPa.
KW - Energetic ionic liquid
KW - Green monopropellant
KW - Hydroxylammonium nitrate
KW - Linear burn rate
KW - Multimode propulsion
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U2 - 10.1016/j.combustflame.2020.04.014
DO - 10.1016/j.combustflame.2020.04.014
M3 - Article
AN - SCOPUS:85086428002
VL - 219
SP - 212
EP - 224
JO - Combustion and Flame
JF - Combustion and Flame
SN - 0010-2180
ER -