Effect of Nozzle Temperature on the Performance of a 1 kW H_2-N_2 Arcjet Thruster  

作　　者：潘文霞 黄河激 吴承康 

机构地区：[1]Institute of Mechanics, Chinese Academy of Sciences

出　　处：《Plasma Science and Technology》2010年第4期473-477,共5页等离子体科学和技术（英文版）

基　　金：supported by National Natural Science Foundation of China (Nos.50836007, 10775164 and 10921062)

摘　　要：A 1 kW-class arcjet thruster was fired in a vacuum chamber at a pressure of 18 Pa. A gas mixture of H2 ： N2 = 2.8 ： 1.5 in volume at a total flow rate of 4.3 slm was used as the propellant with an input power fixed at 860 W. The time-dependent thrust, nozzle temperature and inlet pressure of the propellant were measured simultaneously. Results showed that with the increase in nozzle temperature the thrust decreased and various losses increased. The physical mechanisms involved in these effects are discussed.A 1 kW-class arcjet thruster was fired in a vacuum chamber at a pressure of 18 Pa. A gas mixture of H2 ： N2 = 2.8 ： 1.5 in volume at a total flow rate of 4.3 slm was used as the propellant with an input power fixed at 860 W. The time-dependent thrust, nozzle temperature and inlet pressure of the propellant were measured simultaneously. Results showed that with the increase in nozzle temperature the thrust decreased and various losses increased. The physical mechanisms involved in these effects are discussed.

关 键 词：arcjet thruster nozzle temperature energy conversion experimental measurement 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]