“…Combinations of hypergolic fuel and oxidizer, such as hydrazine or monomethylhydrazine (MMH) for fuel and a mixture of nitrogen tetroxide with approximately 3% nitric oxide (MON3) for oxidizer, eliminate complex ignition systems. In the recent and future cargo spacecraft for the International Space Station [3][4][5][6] and in planetary exploration missions for descent and ascent modules [7][8][9], the bipropellant thrusters keep playing an essential role. The bipropellant thrusters use a combustion chamber generally made of ceramic [10] or high-temperature heat-resistant metal, such as niobium alloy [11,12] or one of the precious metals [13,14].…”