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

作　　者：黄河激[1] 潘文霞[1] 孟显[1] 吴承康[1] 

机构地区：[1]中国科学院力学研究所,高温气体动力学国家重点实验室,北京100190

出　　处：《工程热物理学报》2013年第5期896-898,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.50836007;No.11175226;No.10921062)

摘　　要：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.

关 键 词：电弧加热推力器 推进剂组分 比冲 比功率 效率 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]