离子推力器空心阴极热特性模拟分析  

Thermal analysis of hollow cathodes for ion thruster

作　　者：孙明明[1] 顾佐[1] 郭宁[1] 李娟[1] 

机构地区：[1]兰州物理研究所真空低温技术与物理国家级重点实验室,兰州730000

出　　处：《强激光与粒子束》2010年第5期1149-1152,共4页High Power Laser and Particle Beams

基　　金：真空低温技术与物理国家级重点实验室基金项目(9140C550405090C55)

摘　　要：对离子推力器空心阴极进行了热分析。利用ANSYS有限元软件对阴极罩开启/闭合状态下的空心阴极热启动过程和达到稳态工作时温度场分布进行了模拟,结果表明稳态工作时空心阴极内部能量主要损耗在热阻丝和阴极顶部分,并且阴极罩及热屏是降低空心阴极温度损耗提高其热效率的关键部件,采用阴极罩及热屏后使得空心阴极的总体温度值提升了2.3%-13.2%,其中发射体温度提升2.3%-4.2%,热实验得出的实验数据与模拟结果基本一致,研究结果对空心阴极的优化设计提供参考。This paper describes the thermal behaviour of hollow cathodes as core components in an ion thruster.Warm-up time and steady-state temperature distributions for the cases of the cathode keeper open/closed are simulated using the finite element software ANSYS.The heat of the interior hollow cathode is lost in the heater and orifice plate.Cathode keeper and heat shield are the important components to decrease the heat loss and to improve the heat efficiency.The temperature of hollow cathode with cathode keeper and heat shield increases by 2.3%～13.2% with emitter＇s temperature increasing by 2.3%～4.2%.The simulation results are in agreement with experiment results,providing a reference for the optimum design of the hollow cathode for ion thrusters.

关 键 词：离子推力器 空心阴极 热分析 温度分布 

分 类 号：V439.4[航空宇航科学与技术—航空宇航推进理论与工程]