Experimental Study on Thermal and Catalytic Decomposition of a Dual-Mode Ionic Liquid Propellant

With the increasing of space activities and people’s awareness environmental protection, it is necessary to develop a new non-toxic propulsion system with high performance. Hydroxylammonium nitrate (HAN)/1-ethyl-3-methyl-imidazolium ethylsulfate([Emim][EtSO4]) blend ionic liquid propellant potential replacement high-performance characteristics for hydrazine type propellants, which can be used in both chemical electrical system. This paper introduced thermogravimetric experimental analysis (TGA-DSC) results HAN/[Emim][EtSO4] thermal decomposition catalytic process. Its mass-loss process exothermic under different reaction conditions at heating rate 5K/min~15K/min were studied. Generally, showed that there four characteristic stages during liquids, evaporation water solvent, HAN component, further [Emim][EtSO4], slow loss residual substances. At same time, two peaks observed, respectively corresponded [Emim][EtSO4]. Using catalyst significantly reduce temperature mass. The contents this proved had good application prospect within ignition aerospace thruster.