双模式离子液体推进剂的分解特性与热试车实验研究

硝酸羟胺(HAN)/1 乙基 3 甲基咪唑硫酸乙酯(［Emim］［EtSO4］)混合离子液体推进剂具有绿色无毒、高性能、易电离的特点，既可以应用于化学推进模式，又可以应用于电推进模式，是肼类推进剂的一种理想的替代品.利用热重分析 差示扫描量热法(TGA DSC)研究了HAN/［Emim］［EtSO4］离子液体推进剂的热分解和催化分解过程.研究了其在升温速率为5 K/min~15 K/min时，热分解和催化分解情况下的失重过程和放热过程.失重结果表明，该离子液体推进剂分解过程中，放热曲线表明，分解过程存在两个显著的放热过程使用催化剂可以显著地降低推进剂的分解温度和残余质量.最后，研制了推力为200 mN的模型发动机，热试车结果表明，HAN/［Emim］［EtSO4］离子液体推进剂可以在催化点火条件下实现稳定启动，在空间推进领域具有良好应用前景.

The Decomposition Characteristics and the Hot Fire Test of a Dual-Mode Ionic Liquid Propellant

Hydroxylammonium nitrate (HAN)/1 ethyl 3 methyl imidazolium ethyl sulfate(［Emim］［EtSO4］) blend ionic liquid propellant is a potential replacement with non toxic, high performance and high degree of ionization characteristics for hydrazine type liquid propellants, which can be used in both chemical and electrical propulsion system. This paper introduces the thermogravimetric experimental analysis differential scanning calorimetry (TGA DSC) results of HAN/［Emim］［EtSO4］ ionic liquid propellant with the thermal decomposition and catalytic decomposition process. Its mass loss process and exothermic process under different reaction conditions at a heating rate of 5 K/min~15 K/min are studied. Generally, the mass loss results show that there are four characteristic stages during the decomposition process of the ionic liquids, and the DSC curves show that there are two obvious exothermic processes in the decomposition. Using catalyst can significantly reduce the decomposition temperature of the propellant and the residual mass. Finally, a model thruster with 200 mN thrust is developed. The results of hot fire test show that the propellant can be ignited stably by catalyst. And it has a good application prospect in space propulsion.