推进剂组分对电弧加热推力器性能的影响

Effect of Propellant Composition on the Performance of Arcjet Thrusters

实验研究了以纯氮、纯氢、氨气以及不同体积比氮氢混合气、氨氢混合气作为推进剂时,千瓦级电弧加热推力器的性能。结合理论分析,获得了推进剂组分对推力器性能的影响规律。结果表明,推进剂有效分子量和比热比对推力器冷态性能影响显著。热态下,推进剂组分的热力学性质以及输运性质是影响推力器比冲和效率的关键因素。

Using nitrogen, hydrogen, ammonia and their mixtures as the propellants, the dependence of arcjet thruster performance on the propellant composition was studied. Results show that the cold performance of the arcjet is drastically affected by the effective molecular weight and the adiabatic index of the propellant. On the other hand, the hot performance of the arcjet is mainly affected by the thermodynamic and transport properties of the propellant.