Open AccessPotential of ADN-based Ionic Liquid Propellant for Spacecraft Propulsion
Author(s) -
Yuichiro Ide,
Takuya Takahashi,
Keiichiro Iwai,
Katsuhiko Nozoe,
Hiroto Habu,
Shinichiro Tokudome
Publication year - 2015
Publication title -
procedia engineering
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.32
H-Index - 74
ISSN - 1877-7058
DOI - 10.1016/j.proeng.2014.12.543
Subject(s) - propellant , monopropellant , specific impulse , combustion , ionic liquid , hydrazine (antidepressant) , chemistry , urea , ammonium nitrate , combustor , chemical engineering , ignition system , materials science , aerospace engineering , inorganic chemistry , chromatography , organic chemistry , engineering , catalysis
As an alternative to hydrazine, ammonium dinitramide-based ionic liquid propellant (ADN-based ILP)was developed. It is mixture of the solid powders: ammonium dinitramide, monomethylamine nitrate, and Urea. It has a feature to be able to adjust the performance of monopropellant by change of the compositions because the constituents have different role: oxidizer, fuel, and freezing point depressant. By adjusting the components, it has high specific impulse and fuel rich and low freezing point comparing to hydrazine. The basic combustion characteristics of ADN-based ILP wereinvestigated in the strand burner tests forapplication to thruster. The self-sustainable combustion,the linear burning rates,and the flame temperatureswere shown in the results. The features of the ADN-based ILP were discussed on the basis of the results. As a problem of the thruster application, the ignition in vacuum was also discussed
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