肼催化分解产物电弧推力器的实验研究

Experimental Investigation on Arcjet Using Catalytic Decomposition Products of Hydrazine as Propellant

电弧加热发动机以肼为推进剂不仅可与肼化学推进有高度兼容性,而且可作为在肼化学推力器后以电热增强方式来增大其比冲,因此肼催化分解产物在电弧推力器中的工作性能研究就显得尤为重要。在真空环境下,分别采用氮气、氨气及氮氨氢混合气体(模拟肼的分解产物)和预加热混合气体作为推进剂,系统地测试了电弧推力器在不同工况下的性能参数,对比了不同单一工质对推力器性能的影响,并分析了模拟肼分解产物混合工质的性能变化,比较了混合工质成份变化和改变预热温度对发动机性能的影响,最终得到了混合工质成份变化对发动机性能影响的规律。

The arcjet using hydrazine as a propellant has good compatibility with hydrazine chemical thruster. It can also increase the specific impulse as an electro - thermal enhanced mode after hydrazine chemical thruster in practice. So it is necessary to study the performance of decomposition products of hydrazine for obtaining the optimum conditions. In vacuum environment, performance parameters of arcjet are systematically tested under different working conditions using nitrogen, hydrogen, ammonia, their mixtures （being composed of the catalytic decomposition products of hydrazine） and preheating mixtures as the propellants. The performances of arcjet using nitrogen, hydrogen, ammonia and their mixtures with different proportions as propellant are compared, and the thruster performances varying with the different proportions of the mixtures＇component and the preheating temperature are analyzed. Finally, the effects of different proportions of the mixtures ＂components on the thruster performance are shown.