@inproceedings{8883d70e60c94ba597fd2dad8198e213,
title = "Linear burn rate of monopropellant for multi-mode micropropulsion",
abstract = "Multi-mode micropropulsion is a technology that can enable rapidly composable small satellites with unprecedented mission flexibility. To maximize mission flexibility a multi-mode micropropulsion monopropellant must be shared between the chemical and electric propulsion modes. Previous research has identified a promising monopropellant that is both readily catalytically exothermically decomposed (chemical mode) and electrosprayable (electric mode). In this work the linear burn rate of this monopropellant is determined and used to aid the design of a microtube catalytic chemical thruster. Experiments with a pressurized fixed volume reactor are used to determine the linear burn rate. Benchmark experiments use a 13-molar mixture of hydroxylammonium nitrate and water and show agreement to within 5% of literature data. The multi-mode monopropellant is a double-salt ionic liquid consisting of 41% 1-ethyl-3-methylimidazolium ethyl sulfate and 59% hydroxylammonium nitrate by mass. At the design pressure of 1.5 MPa the linear burn rate of this propellant is 26.4 ± 2.5 mm/s. Based on this result, the minimum flow rate required for a microtube with a 0.1 mm inner diameter within the pressure range tested is between 0.12 and 0.35 mg/s.",
author = "Mundahl, {Alex J.} and Berg, {Steven P.} and Rovey, {Joshua L.}",
note = "Funding Information: The authors would like to thank the researchers of the Aerospace Plasma Laboratory for their assistance throughout this experiment and providing insightful information. The authors thank the technicians within the department machine shop for their assistance in the manufacturing process of this experiment. Support for this work was provided through the NASA Marshall Space Flight Center, NASA grant NNM15AA09A, and the Air Force University Nanosatellite Program through the Utah State University Research Foundation, grant CP0039814. Additional support was provided by NASA Goddard Space Flight Center through the NASA Undergraduate Student Instrument Project grant NNX16AI85A, and the University of Missouri System Fast Track Program. Publisher Copyright: {\textcopyright} 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; 54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018 ; Conference date: 09-07-2018 Through 11-07-2018",
year = "2018",
doi = "10.2514/6.2018-4970",
language = "English (US)",
isbn = "9781624105708",
series = "2018 Joint Propulsion Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "2018 Joint Propulsion Conference",
}